An aircraft (101) includes a rotor blade (107) and a rotor hub system (301). The rotor hub system (301) includes a lead-lag damper (303) having a rod end (315) and being operably associated with the rotor blade (107); a blade adapter (307) having a first arm (309) and an opposing second arm (311); a pin (316) carried by the blade adapter (307) and configured to secure in position via the first arm (309) and the second arm (311); and an actuator (703) secured to the pin (316) and configured to adjust the position of the lead-lag rod end (315) relative to the first arm (309) and the second arm (311).
ADJUSTABLE BLADE-TO-HUB LEAD-LAG DAMPER ATTACHMENT
EINSTELLBARE BEFESTIGUNG FÜR BLATT-ROTORKOPF-SCHLAG-/SCHWENK-DÄMPFER
FIXATION RÉGLABLE D'AMORTISSEUR DE TRAÎNÉE PALE-MOYEU
2015-11-25
Patent
Electronic Resource
English
The Inter-2-Blade Lead-Lag Damper Concept
British Library Conference Proceedings | 2022
|