Patent ID: 7982328

Claim:
An aircraft emergency supply unit comprising: a ram-air turbine driven by an air stream and surrounded substantially concentrically by a casing forming a flow channel, the ram-air turbine positioned within the casing such that the spatial position of the ram-air turbine remains unchanged when the aircraft emergency supply unit is selectively brought into a standby mode or into an operating mode, an energy converter for at least partly maintaining the functioning of at least one of a hydraulic system and an electrical system on board an aircraft in an emergency situation, wherein the energy converter is driven by the ram-air turbine in the operating mode and is directly coupled to the ram-air turbine via a drive shaft, at least one air inlet through which the air stream is delivered to the ram-air turbine in the operating mode, at least one shut-off member for closing the air inlet, which in the standby mode of the aircraft emergency supply unit his into the outer contour of the aircraft to optimise the aerodynamics, an air outlet, at least one shut-off member for closing the air outlet, which in the standby mode of the aircraft emergency supply unit fits into the outer contour of the aircraft to optimise the aerodynamics, a first inlet channel, and a second inlet channel, the first and the second inlet channel opening into the flow channel and having a smaller cross section than the flow channel.