Patent ID: 9452829
Filing Date: 2016-09-27
CPC Classification: B64C,Y02T

Claim Text:
1. A method for controlling rotor blades of a co-axial counter-rotating rotor assembly of an aircraft including a first rotor co-axial with a second rotor, comprising: identifying a first zone of rotor rotation angles of the co-axial counter-rotating rotor assembly, the first zone defining a range of rotor rotation angles corresponding to an up-flow of air to the coaxial rotor assembly, and the remainder of the rotor rotation angles other than the first zone of rotation angles being defined as a second zone; receiving a yaw command to adjust a yaw moment of the aircraft; and applying a different rotor blade angle change to rotor blades in the first zone than a rotor blade angle change applied to rotor blades in the second zone to adjust the yaw moment of the aircraft according to the yaw command.