Helicopter rotor system and method.

摘要

A rotor hub system (10) for a helicopter in which the rotor hub (12) and pitch housing (14) are fabricated predominately of composite material, the flap hinge, pitch hinge and lead-lag hinge contain elastomeric bearings and one step blade folding in either the forward or aft direction using the same drive system. The rotor hub (12) includes closed loop straps which define generally opposed lugs of the flap hinge, and the pitch housing (14) includes a pair of closed loop straps which define the lugs of the lead-lag hinge and a lug of the flap hinge. The use of composite materials as the predominant material of the rotor hub (12) and the pitch housing (14) results in a highly load redundant structure permitting a reduction in size and number of parts, a reduction in drag, and an increase in reliability and safety.