Rib Design for a Flexible Trailing Edge of Aircraft

The work in this report provides a detailed design and mechanical simulation rib design in flexible trailing edge/morphing wing aircraft. Initially the report initially a brief background knowledge on flexible trailing edge and how to validate design and design changes through simulation software. The report is then divided into two main components that were undertaken during this project. The first part encompasses a design of a rectangular beam in the morphing section. This was achieved by conceptualizing two designs which can be distinguished by their various types of supports. The second part entailed a design of internal structure for the morphing wing. A total of six designs in addition to the initial design were conceptualized which included variations of number of circular structures ranging from two to 4 and variations in locations of these structures. All these designs were 3-D modeled in CATIA-V5 software and were verified by performing ANSYS Finite Element analysis software on these respective 3-D CAD models. The report then provides a detailed comparison between these designs and ultimately provides final design for each component. Finally, the report provides few brief concepts on how this project can be applied and improved in future.