The project deals with the development of high bandwidth electrical helicopter flight control actuators. The actuators are based on the use of active torque plate concept. Torque plates, integrated in the blade roots, pitch the blades to proper attitude by twisting. The plate system is completely solid state resulting in a much cleaner hub without swash plates, linkages or bearings. The active elements have extremely high efficiencies leading to very low power consumption and high break frequencies. The performance of the active plates is predicted using laminated plate theory. Analytical models are refined to accurately account for torque-plate nonlinearities. The performance of torque elements is compared to hydraulic and other electromechanical actuation systems.
