Thomas H Cavanaugh

US Patent:

47385928, Apr 19, 1988

Filed:

Sep 28, 1984

Appl. No.:

6/656063

Inventors:

Thomas J. Cavanaugh - Upper Darby PA

Assignee:

The Boeing Company - Seattle WA

International Classification:

B64C 2735

US Classification:

416140

Abstract:

A system for folding a helicopter rotor blade in which the lead-lag damper is mounted to the rotor blade spar, attached to the pitch housing and centered at the vertical pin flap hinge axis. This design of the lead-lag damper corresponding to a specially designed cam has a single actuator used to fold the rotor blade by sequentially engaging the cam with the actuator and lead-lag damper. Connected to the lead-lag damper is a lead-lag damper linkage assembly which is located in the operative position of the rotor blade so that flight loads are transferred directly to the pitch housing thereby uncoupling the actuator and cam from the path of these loads. In addition, this linkage is connected over center during blade folding so that the rotor blade cannot be back driven.