Designing and testing shape memory alloy actuators for smart aircraft wings

The pursuit of enhanced aircraft performance through shape-adapting smart wings ne- cessitates lightweight, reliable, and efficient actuation systems. While Shape Memory Alloys (SMAs) offer a high power-to-weight ratio, a primary challenge remains in the validation of robust bidirectional control mechanisms within realistic airframe structures. This study presents a complete methodology for the design, additive manufacturing, and experimental testing of an aircraft flap actuated by an antagonistic SMA spring system. The core novelty lies in the holistic experimental validation of this dual-sided mechanism, which is fully integrated within a 3D-printed NACA 4412 airfoil, demonstrating a practical pathway from concept to functional prototype. A corresponding Finite Element Analysis was developed and validated to verify structural integrity under measured operational loads. Experimental testing demonstrated highly controllable and repeatable bidirectional flap deflections, achieving a maximum of 30^◦ of upward actuation at 12 V with response times under 20 s. The structural analysis confirmed the prototype's robustness, with the highest stress concentrations correctly identified at the hinge. This work provides a validated, low-cost framework and critical performance data, offering a foundational step towards the practical implementation of advanced smart wing technologies. The findings underscore the viability of the antagonistic SMA design while also highlighting key operational challenges, such as the need for active cooling to improve reset times, which are critical for future development. This research serves as a comprehensive case study, bridging the gap between theoretical SMA capabilities and tangible aerospace application.