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).
申请公布号
EP2947007(A1)
申请公布日期
2015.11.25
申请号
EP20150168540
申请日期
2015.05.20
申请人
BELL HELICOPTER TEXTRON INC.
发明人
RAUBER, RICHARD E.;YUCE, MITHAT;PARHAM, THOMAS C.;NEWMAN, THOMAS J.;WIINIKKA, MARK A.