Analytical and experimental verification of morphing bistable composites for aerospace thermal management

The use of composite laminates in aerospace applications presents the opportunity to exploit their multifunctionality. Thermal management scenarios create unique possibilities for integrating composites, particularly where thermal loading facilitates passive actuation. These composite laminates, when constructed in specific geometries and ply orientations, possess the ability to morph between stable configurations. The applied load that triggers the morphing can be electrical, mechanical, or thermal; this paper focuses on thermal approaches. The literature contains little data on the experimental transition of unstable geometry; this nonlinear response of the force versus displacement graph and the negative slope are unique quantities integral to understanding the composite’s response to the external loading conditions. We aim to help fill this gap through the testing of the composites under various loading conditions, boundary conditions, and geometric configurations. With the aim to apply this knowledge in the integration of these composite laminates within a thermal management case, utilizing the already present loads within a system.