Patent ID: 6200096
Filing Date: 2001-03-13
Classification: B64C,Y02T

Abstract:
A flap actuation system for a helicopter rotor blade, the rotor blade having a root end, a tip end, a trailing edge and a flap hinged to at least a portion of the trailing edge, the flap being pivotable about a pivot axis, the flap actuation system comprising:at least one supply line mounted within the rotor blade and extending outward from the root end, the supply line adapted to channel pressurized fluid;a valve attached to the at least one supply line for controlling a flow of fluid along the supply line;a controller adapted to receive signals indicative of the current state of the flap, the controller providing a signal to the valve for controlling the operational state of the valve; andat least one actuator fluidly connected to the at least one supply line, the actuator having a displacement member and a head member, the head member being engaged with the flap and adapted to pivot the flap about its pivot axis when pressurized fluid is conveyed through the at least one supply line.