Abstract
Compliant morphing structures have been explored in aircraft as potential alternatives to rigid hinge-based mechanisms because of their ability to undergo large deformations without complicated assemblies. The simple geometry, high strength-to-weight ratio, and selective stiffness of bistable composite laminates make them highly suitable for use in morphing structures. However, rectangular asymmetric laminates with one edge clamped lose their bistability at low aspect ratios (free edge length to clamped edge length). Introducing multiple slits parallel to the free edge of these laminates has previously been shown to enable natural curving, thereby preserving their bistability. In this work, we characterize the behavior of a slitted bistable laminate under aerodynamic loading. The laminate is mounted to a bluff body leading edge inside a wind tunnel. The lift and drag forces acting on the two stable states of the slitted laminate are measured at two different flow speeds of 10 m/s and 20 m/s, and angles of attack ranging from −10 degrees to +10 degrees. We compare these results to those of a conventional bistable laminate with the same geometry to understand how the addition of slits affects the associated aerodynamics.
