This work introduces a novel structural concept for morphing wings, based on carbon-fiber reinforced polymer (CFRP) lattice structures. Conventional wing spars and ribs are replaced by CFRP rods, which are arranged with varying orientation and distribution within a load-carrying wing skin. A new structural parametrization is introduced to define the internal lattice structure. By adapting the orientation and distribution of the rods, the aeroelastic behavior of the wing is tailored. The material of the structure is thereby arranged in a structurally efficient manner, removing any excess material and reducing the mass of the wing. Furthermore, the arrangement of the rods promotes shape morphing, which is used for active flight control obtained with an integrated actuation mechanism. A demonstrator was fabricated to evaluate the actuation integration and morphing performance. To assess the lightweight and morphing potential of the wing, an optimization considering the fluid–structure interaction of the wing is carried out. For the investigated wing, the parameters describing the rod arrangement, the skin layup, and the actuation are optimized. A lightweight lattice morphing wing with high load-carrying capabilities and sufficient rolling moment coefficient compared to existing morphing wings was achieved.

这项工作引入了一种基于碳纤维增强聚合物（CFRP）晶格结构的新型机翼变型结构概念。常规机翼的翼梁和肋骨被CFRP杆代替，CFRP杆在载荷的机翼蒙皮中以不同的方向和分布进行布置。引入了新的结构参数化来定义内部晶格结构。通过调整杆的方向和分布，可以调整机翼的气动弹性性能。因此，结构的材料以结构上有效的方式布置，从而去除了多余的材料并减小了机翼的质量。此外，杆的布置促进了形状变形，该变形用于通过集成致动机构获得的主动飞行控制。制作了一个演示器来评估促动集成和变形性能。为了评估机翼的轻量化和变型潜力，进行了考虑机翼流固耦合的优化。对于所研究的机翼，描述杆布置，蒙皮铺设和致动的参数已得到优化。与现有的变形机翼相比，实现了一种轻质的格子变形机翼，具有较高的承载能力和足够的侧倾力矩系数。