Patent ID: 7658066

Claim:
An actuation device for the actuation of an aerodynamic adjustment surface of an aircraft, landing gear or another aircraft or surface vehicle actuator, comprising an electrohydraulic actuator ( 1 ) having a servo control cylinder ( 2 ), a pump ( 3 ) for pressure fluid action on the servo control cylinder ( 2 ) as well as an electric motor ( 4 ) for the actuation of the pump ( 3 ), with the electric motor ( 4 ) having a liquid cooling, wherein a leak flow ( 13 ) of the pump ( 3 ) is guided via a leak passage ( 17 ) through the electric motor ( 4 ) for the cooling of the electric motor ( 4 ), wherein said electric motor ( 4 ) has a seal sleeve ( 19 ) extending between the rotor and stator of the electric motor and sealing the winding of the electric motor in a fluid tight manner with respect to the leak flow, wherein said leak flow is guided within the seal sleeve ( 19 ) from a first rotor end face to an oppositely disposed second rotor end face, wherein the leak flow leaving said seal sleeve ( 19 ) and the electric motor ( 4 ) is guided into a reservoir ( 22 ) which has a bellows ( 24 ) received in a reservoir housing ( 23 ) with the leak flow ( 13 ) being fed into and/or stored in a gap defined outside the bellows ( 24 ) between said reservoir housing ( 23 ) and the bellows ( 24 ).