Patent ID: 9248909
Filing Date: 2016-02-02
CPC Classification: B64C,H02K,Y02T

Claim Text:
1. A main rotor system of an aircraft comprising: a first rotor coupled to a transmission and configured to rotate about a first axis in a first direction; a second rotor coupled to the transmission, the second rotor being configured to rotate about the first axis in a second direction, wherein at least the first rotor includes an individual blade control system (IBCS) configured to adjust a pitch of each of a plurality of blades of the first rotor independently; a standpipe fixedly attached to the aircraft, the standpipe being arranged such that the first rotor and the second rotor rotate relative to the standpipe; and at least one slip ring configured to transmit at least one of electrical power or a control signal to the at least one IBCS.