Patent ID: 8939725
Filing Date: 2015-01-27
Classification: B64C

Abstract:
1. A rotor system for an aircraft including a rotor ( 1 ) with a rotary structure ( 7 , 7 ′) mounted rotatable about a rotation axis ( 8 ) and supporting a proximal end ( 9 ) of at least one rotor blade ( 3 ), wherein the rotor system comprises at least one jet turbine ( 4 , 4 ′) for providing pressurised exhaust gas to the rotary structure ( 7 , 7 ′), the rotary structure ( 7 , 7 ′) having at least one jet nozzle outlet ( 6 ) and at least one jet stream duct ( 5 , 5 ′) for transporting the pressurised exhaust gas from the jet turbine ( 4 , 4 ′) to the jet nozzle outlet ( 6 ) to cause rotation of the rotary structure ( 7 , 7 ′) by expelling the pressurised exhaust gas through the nozzle outlet ( 6 ), the rotor system having a support structure ( 20 ) for attaching the rotor system to an aircraft body, wherein only the rotary structure ( 7 , 7 ′) and not the rotor blade ( 3 , 3 ′) comprise a jet stream duct ( 5 , 5 ′) and a nozzle outlet ( 6 ), the rotor system comprising an adjuster for adjusting yaw of the aircraft body relative to the earth, the adjuster being shaftless connected to the rotary structure ( 7 ), and further comprising a magnetic coupling between the support structure and the rotary structure ( 7 ), wherein the magnetic coupling comprises an integrated electromagnetic motor ( 51 ) rotationally coupling the rotary structure ( 7 ) to the support structure ( 20 ), wherein the electromagnetic motor comprises at least one permanent magnet ( 18 ) on the rotary structure ( 7 ) and at least one electromagnet ( 19 ) on the support structure ( 20 ), wherein the electromagnetic motor controls the yaw by advancing or retarding relative rotation between the at least one electromagnet on the support structure and the at least one permanent magnet on the rotary structure.