Static aeroelastic modeling and parametric study of stacking sequence for laminated composite missile fins

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2018
Aslan, Göktuğ Murat
In this thesis, a surface-to-surface missile model with laminated composite fins is examined with respect to one-way static aeroelastic response under constant supersonic flight conditions. Two different modified double wedge fins or control surfaces using for control actuation system of a missile are investigated and compared in terms of aerodynamic and linear structural characteristics in order to minimize tip deflection. A serial set of steady-state supersonic Computational Fluid Dynamics (CFD) analyses at different angles of attack are conducted in order to obtain pressure distribution causing the structural deflection or failure on fins having modified double-wedge cross-sections. Grid refinement study is also performed for CFD analysis part. Control surface models are manufactured and tested in supersonic wind tunnel at a certain angle of attack and Mach number in order to observe shock waves on control surfaces during the flight. By using aerodynamic loads due to pressure distribution on fins, linear structural analyses with an algorithm written in Matlab® are executed in Nastran®. This algorithm examines the different stacking sequence of the laminated composite control surfaces in order to reduce tip deflection by considering four different failure criteria. Three structures with different stacking sequences not failing under maximum aerodynamic loads in structural analyses are manufactured and tested for both control surface models in order to compare and verify the maximum tip deflection results of Finite Element Method.

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Citation Formats
G. M. Aslan, “Static aeroelastic modeling and parametric study of stacking sequence for laminated composite missile fins,” M.S. - Master of Science, Middle East Technical University, 2018.