Abstract
An investigation to observe the morphing capabilities of actuated macro fiber composite patches on multi-curved aircraft surfaces was conducted. Inattentive positioning of these patches can reduce desired surface deflection and mitigate aerodynamic performance. An initial study was performed on a 2-D fiber reinforced airfoil to observe the morphology of the cross-section when macro fiber composite patches were actuated in different chordwise positions. This was achieved through iterative finite element analysis using a thermal expansion method analogous to piezoelectric effects. The study was adapted to a complex 3-D wing surface where positioning and fiber orientation were considered. The kinematic performance was evidently affected for multi-curved versus more curvy-linear structures, where reduced surface curvature was favorable for more trailing edge deflection. In addition, effects of non-linearity of piezoceramic composites were observed in tandem on these complex surfaces using digital image correlation. Hysteresis and creep effects by virtue displayed kinematic behavior as a function of time and structural geometry. For a multi-curved wing, the residual strain due to hysteresis and creep were less apparent than for a reduced multi-curved surface.
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The authors would like to thank the STTR program under the Air Force Office of Scientific Research for the funding.
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Tran, B., Ifju, P.G., Mennu, M.M., Brenes, A., Shbalko, S. (2021). Applying Macro Fiber Composite Patches to Morph Complex Aircraft Structure. In: Singh, R.P., Chalivendra, V. (eds) Mechanics of Composite, Hybrid and Multifunctional Materials , Volume 6. Conference Proceedings of the Society for Experimental Mechanics Series. Springer, Cham. https://doi.org/10.1007/978-3-030-59868-6_15
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