TY - GEN
T1 - Applying Macro Fiber Composite Patches to Morph Complex Aircraft Structure
AU - Tran, B.
AU - Ifju, P. G.
AU - Mennu, M. M.
AU - Brenes, A.
AU - Shbalko, S.
N1 - Publisher Copyright:
© 2021, The Society for Experimental Mechanics, Inc.
PY - 2021
Y1 - 2021
N2 - 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.
AB - 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.
KW - Digital image correlation
KW - Finite element method
KW - Macro fiber composite
KW - Multicurve structure
UR - http://www.scopus.com/inward/record.url?scp=85106185534&partnerID=8YFLogxK
U2 - 10.1007/978-3-030-59868-6_15
DO - 10.1007/978-3-030-59868-6_15
M3 - Conference contribution
AN - SCOPUS:85106185534
SN - 9783030598679
T3 - Conference Proceedings of the Society for Experimental Mechanics Series
SP - 99
EP - 106
BT - Mechanics of Composite, Hybrid and Multifunctional Materials - Proceedings of the 2020 Annual Conference on Experimental and Applied Mechanics
A2 - Singh, Raman P.
A2 - Chalivendra, Vijay
PB - Springer
T2 - SEM Annual Conference and Exposition on Experimental and Applied Mechanics, 2020
Y2 - 14 September 2020 through 17 September 2020
ER -