Mechanical Part 2: Aeroelastic Flex Mitigation — Concentric Carbon Spar Architecture

Initial flight testing revealed wing flexing under sharp turns using two 10 mm carbon spars. Rather than adding drag-inducing external struts, the primary load-bearing architecture was expanded to 3 parallel lines. Secondary 8 mm outer-diameter carbon tubes were press-fitted inside the primary 10 mm (8mm ID) spars, creating a Dual-Layer Concentric Carbon Spar Architecture. This modification increased torsional stiffness exponentially while adding only +50 g to the aircraft mass.