FlexFoil™ Compliant Control Surfaces
FlexFoil™ Compliant Wing superior to Hinged Flaps
FlexFoil™ variable geometry control surfaces represent a major improvement over conventional aircraft flaps. By exploiting the natural elasticity of aviation grade materials the FlexFoil™ control surface changes the camber of a wing during flight by shape morphing rather than through the heavy and cumbersome mechanisms of conventional wing assemblies. Shape morphing performs the large controlled deformations (from -9° to + 40°) needed for landing and takeoff without separating from the rest of the wing. Our new approach also permits discrete span-wise twist of the compliant edge at high response rates (30 degrees/sec.) to reduce induced drag and withstand external loads (air loads, inertial loads etc.), yet it is strong and stiff with very small and distributed strains on the mechanical structures and control surfaces.
FlexFoil™ is an Aviation First
FlexSys has developed the world's first seamless, hinge-free shape morphing wing whose trailing and leading edges can adapt on demand to variable flight conditions in real time. With US Air Force funding, FlexSys has developed proprietary design methods for morphing control surfaces
FlexFoil™ Adaptive Compliant Wings Provide Significant Fuel Savings
In addition to this major innovation in aircraft control surface design an even more far reaching impact of this technology is drag reduction in the range of 5% to 12% for long-range fixed wing aircraft, and that represents huge savings in fuel consumption. Studies by NASA Dryden Flight Research Center have shown that even a one percent reduction in drag for the U.S. fleet of wide-body transport aircraft could result in savings of approximately 200 million gallons per year.
FlexFoil™ allows for a smooth continuous flight surface
Bridging the gaps between flap and wing, FlexFoil™ doesn't separate from the rigid part of the wing unlike conventional flaps that violently disrupt the air flow when they deploy. FlexFoil™ maintains a seamless connection even at its edges. Flexible articulating transition surfaces keep the fixed parts of the wing connected to the shape morphed control surface maintaining a continuous trailing edge that significantly reduces airframe noise.
US Patents: 5971328, 6491262, 7384016 B1, European Patents: 1047593, 1603798, DE 69934210T2 — other US and intl. patents pending.