Method of fabricating a helicopter rotor system

Details Method of fabricating a helicopter rotor system Method of fabricating a helicopter rotor system

1988-08-31

1989-09-26

Goldberg, Howard N.

Metal working

Means to assemble or disassemble

Puller or pusher means, contained force multiplying operator

291568B, 29428, 416134A, B21K 300

Patent

active

048689629

ABSTRACT:
A rotor hub system for a helicopter is 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 is employed. The rotor hub includes closed loop straps which define generally opposed lugs of the flap hinge, and the pitch housing 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 and the pitch housing 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.

REFERENCES:
patent: 4108508 (1978-08-01), Clinard, Jr.
patent: 4273601 (1981-06-01), Weingart
patent: 4293276 (1981-10-01), Brogdon et al.
patent: 4321013 (1982-03-01), Schwarz et al.
patent: 4542567 (1985-09-01), McArdle et al.
patent: 4776076 (1988-10-01), Frank et al.

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