Application of the aeroelastic analysis and design framework developed at Delft University of Technology to a design of two aeroelastically tailored composite wings for a flying demonstrator is presented. The objective of the design process is to minimize structural mass of the wing while maintaining a target cruise shape. For this purpose, the jig shape of the wing is parameterized and becomes an integral part of the optimization, while the cruise shape is maintained by means of a constraint. Additionally strength, buckling, aeroelastic stability constraints, and a number of other design requirements have been introduced to obtain a feasible and flight-worthy design. Two wing types were designed: the reference wing and the tailored wing. The difference between the two wings is in the definition of the laminates comprising each wing. The reference wing was designed with symmetric-balanced laminates, while symmetric-unbalanced laminates were used for the tailored wing. The comparison is performed in terms of laminate stiffness and thickness distribution along the span, jig twist, and the aeroelastic response covering elastic deformations, aerodynamic load distribution, and wing root loads, showing a significant mass reduction for the tailored wing compared to the reference wing.

介绍了代尔夫特理工大学开发的气动弹性分析和设计框架在为飞行演示者设计的两个气动弹性复合材料机翼的设计中的应用。设计过程的目的是在保持目标巡航形状的同时，最小化机翼的结构质量。为此，对机翼的夹具形状进行参数化并成为优化的组成部分，同时通过约束条件来保持巡航形状。另外，强度，屈曲，气动弹性稳定性约束以及许多其他设计要求已被引入以获得可行且值得飞行的设计。设计了两种机翼类型：参考机翼和量身定制的机翼。两个机翼之间的区别在于包括每个机翼的层压板的定义。参考机翼采用对称平衡的层压板设计，而对称不平衡的层压板用于定制机翼。根据层压板的刚度和厚度分布，跨距，夹具扭曲以及覆盖弹性变形，气动载荷分布和机翼根部载荷的气动弹性响应进行比较，与参考机翼相比，定制机翼的质量显着降低。