Abstract: Individual blade control of a helicopter rotor is accomplished by rotation of a mast (10) about a standpipe (12) where an individual blade (16) is coupled to the mast through a hub (18). Pilot input signals are transmitted by fly-by-optic transmission lines (14) through a fiber optic slip ring (40,42) to signal generators (134, 136, 138) for each of three sections of triplex actuators (76-79) coupled to individual rotor blades. Hydraulic fluid for positioning each of the actuators (76-79) is provided by electrohydraulic power packages (88, 90 and 92) where each package includes a pump and alternator. As each blade rotates about the mast (76) the pitch angle changes by individualizing the output of the signal generators (134-138) for each actuator.

Abstract: A helicopter having a mast 50 which drives a rotor and which is driven from a transmission 16 has a swashplate 10 individually linked to pitch horns on each rotor blade. At least four control channels 11-15 are coupled to the swashplate. Three channels may control the attitude and position of the swashplate. The control channels 11-15 are actuated in response to pilot commands transmitted by means including mechanical, optical or electrical systems. A separate power unit 21-25, 31-35 supplies each control channel. Each power unit is directly driven by the transmission 16. Means 11c-15c applies control of the swashplate 10 from among the control channels 11-15.