Implementation of SMA wires in ultra-lightweight deployment/deflection mechanisms for aerospace and unmanned aerial vehicles

This paper presents the implementation of SMA wires in ultra-lightweight deployment/deflection mechanisms within the aerospace and unmanned aerial vehicle (UAV) fields. First, an SMA-HINGE is designed, simulated, and experimentally validated; it effectively converts the contraction of the SMA wire into rotation within the range of [0, \(\pi \) $\pi$ ]. The developed SMA-HINGE is then utilized for deploying a satellite’s solar array, including both a multistage deployment mechanism and a folding fan-inspired deployment mechanism. Furthermore, a redesign of the SMA-HINGE is conducted by incorporating a pair of SMA wires, demonstrating exceptional actuation performance for the deflection of the UAV’s rudder surface. Notably, the total weight of the SMA wires employed in actuating the aforementioned deployment/deflection mechanisms is a mere 1 g, 1.6 g, and 1 g, respectively.