Rotorcraft Leading Edge Technology
The FlexSys variable geometry leading edge for rotorcraft creates a seamless upper surface and has a sliding joint on the lower surface. The structure is made of Titanium and is capable of 10° LE droop at once per rev. The compliant system is designed to withstand air loads and inertial loads (600gs) for 220 million morphing cycles. This technology enables the delay of dynamic stall on the retreating blade and requires 126 Watts/ft span with a weight of 4.3Lbs/ft.
FlexSys Adaptive Leading Edge for Rotorcraft. U.S. Patents 5971328, 6491262, 7384016 B1, Brazilian patent PI 0408101-3, Canadian 2,518,080, European 1047593, 1603798, DE 69934210T2, Several other US and Intl. Patents Pending.
Rotorcraft Trailing Edge Technology
The FlexSys variable geometry trailing edge for rotorcraft is capable of 1 cycle/rev large deflection for cyclic control and 5 cycles/rev for vibration control. The 10% chord FlexSys compliant flap has equivalent aero performance as a 15% conventional flap and consumes 20% less power than a conventional TE flap. These benefits give FlexSys the technological edge for rotorcraft active blade technology.
Deflected Rotorblade and Flap Deflection Schedule. U.S 5971328, 6491262,7384016 B1, Brazilian patent PI 0408101-3, Canadian 2,518,080, European 1047593, 1603798, DE 69934210T2, Several other US and Intl. Patents Pending.