Patent ID: 9039373
Filing Date: 2015-05-26
Classification: B64C

Abstract:
1. A blade-pitch control system for controlling a pitch angle of each of a plurality of blades on an aircraft rotor, the blades being rotatably connected to a yoke for rotation with a rotor mast, the control system comprising: a swashplate assembly having a non-rotating portion and a rotating portion; a feedback lever associated with each blade, each lever being pivotally mounted to the rotating portion of the swashplate assembly, an input arm and an output arm extending from opposing sides of a pivot axis of the lever, the arms moving in opposite directions when the lever is pivoted relative to the rotation portion; a pitch link connecting the output arm to a pitch horn of a corresponding blade; a feedback link connecting the input arm to the yoke; and a pivot shaft for pivotal mounting of each lever, each pivot shaft extending radially outward from the rotating portion of the swashplate assembly; wherein flapping motion of the yoke causes motion of the feedback link, and this motion causes corresponding rotation of the lever and motion of the pitch link, providing for selected pitch-flap coupling between flapping motion of the yoke and pitch motion of the blades.