Structural and dynamic analysis of a seamless aeroelastic wing

This paper presents an investigation into the dynamic and aeroservoelastic behavior of a seamless aeroelastic wing (SAW) structure for a small air vehicle. Attention was initially given to the design of an internal actuation system and its integration with a hingeless flexible trailing edge (TE) control surface. The SAW control section design has two innovative features, a torque tube actuation mechanism (TTAM) and a sliding TE of the wing skins. These design features allow for the SAW to have a local camber variation and wing twist in a favorable shape to meet the flight performance requirement. Based on the design features and previous optimal design of the wing box structure, the current investigation has been focused on the study of the dynamic and aeroservoelastic behavior of the SAW by using FWM. An experimental model was built to demonstrate and test the TTAM system. Some key parameters such as the stiffness of the actuation system were identified from vibration test data of the TTAM. They were used to update the FE model and analyze the dynamic response of the SAW. The results show that the SAW satisfies the design requirements from a structural point of view.