发明名称 ROTOR SYSTEM WITH PITCH FLAP COUPLING
摘要 An articulated rotor system with a servo-flap rotor control system locates the focal point of a blade retention spherical elastomeric bearing inboard of a joint in the servo-flap pitch control tube which separates the flap hinge and supports the servo-flap pitch control tube on a single pivot bearing within a blade retention spindle. Rotor blade flapping produces relative movements between the servo-flap pitch control tube and the blade retention spindle which is converted through a servo-flap drive linkage into servo-flap pitch motions to provide flap/pitch coupling which reduces steady and transient blade flapping.
申请公布号 EP2084055(A4) 申请公布日期 2014.01.01
申请号 EP20070875057 申请日期 2007.11.12
申请人 SIKORSKY AIRCRAFT CORPORATION 发明人 SCHMALING, DAVID N.;CABRERA, PEDRO L.
分类号 B63H1/06;B64C27/32;B64C27/35;B64C27/72 主分类号 B63H1/06
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