Aeroelastic Modelling and Testing of a Thin Laminated Composite Missile Fin/Wing

2017-06-09
Aslan, Göktuğ
Kırımlıoğlu, Serdar
Kurtuluş, Dilek Funda
Missile fins or wings exposed to different coupled aerodynamic loads during the mission or flight at subsonic and supersonic velocity profile. Aerodynamic loads varying with the angle of attack and the velocity profile may cause some structural fatigue and failure problems. In order to achieve such problems, high strength materials such as composites are required. In this work, a laminated composite missile fin was investigated in terms of the strength varying with the aerodynamic profile. The fiber orientation of the laminated fin/wing will be optimized to obtain a high strength configuration. The double wedge airfoil profile was used in Computational Fluid Dynamics (CFD) and structural analysis. A set of computational fluid dynamic and structural finite element analysis had been done in order to optimize the composite configuration. During the analyses, fluid structure interactions were observed for the different boundary conditions. © 2017 American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
Citation Formats
G. Aslan, S. Kırımlıoğlu, and D. F. Kurtuluş, “Aeroelastic Modelling and Testing of a Thin Laminated Composite Missile Fin/Wing,” presented at the 8th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference, 2017, Denver; United States, 2017, Accessed: 00, 2021. [Online]. Available: https://hdl.handle.net/11511/85883.