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Morphing aircraft structures offer opportunities for the development of new aerospace technologies. A benchtopscale model of a morphed leading edge composed of a carbon nanotube-polyurethane stretchable skin and 3D printed substructure was designed and developed [1]. To improve the overall accuracy of the leading edge shape, the design of the sub-structure is to be optimized. This paper describes the material characterization of the 3D printed sub-structure. The properties of the sub-structure material were determined through flexural testing of 3D printed coupons. The material properties were then calibrated through finite element modeling of the test. Finally, these properties were applied to the model of a test specimen of variable thickness in order to validate their applicability for finite element analysis of increasingly complex shapes, such as those found in the morphed leading edge benchtop model.

Experimental Testing, Modeling, and Simulation of 3D Printed Composite Material for Morphing Wing Application