A method, apparatus, system, and computer program product for managing pumps in an aircraft. Flight information about an operation of the pumps in a pump package in the aircraft is received by a computer system. The flight information is received from the aircraft. A number of times that an abnormal switching occurred for the pumps within a window of consecutive flights is determined by the computer system when the abnormal switching is identified from the flight information. A set of actions is performed by the computer system when the abnormal switching occurred a number of times for the pumps within the window of consecutive flights that exceeds a set of thresholds for the abnormal switching that is considered healthy for the pumps.

The jet engine comprising a ramjet air path extending from an intake, into a combustion chamber, and out an exhaust nozzle, a fuel inlet leading into the combustion chamber, an oxidizer inlet leading into the combustion chamber and a partition being operable to selectively close the ramjet air path upstream of the combustion chamber to allow operation of the jet engine in rocket mode and open the ramjet air path to allow operation of the jet engine in ramjet mode.

An auxiliary power unit system of an aircraft includes an auxiliary power unit (APU), a cooling unit for the APU including a heat exchanger, an air inlet in communication with the APU and/or with the cooling unit, an air inlet door unit located at the air inlet, a first duct configured to draw air into the APU and having an entrance in communication with the air inlet, a second duct having an entrance in communication with the air inlet, the heat exchanger being at least partially located within the second duct, an air turbine located within the second duct downstream of the heat exchanger, and an electrical generator coupled to the air turbine.

A method, apparatus, system, and computer program product for managing pumps in an aircraft. Flight information about an operation of the pumps in a pump package in the aircraft is received by a computer system. The flight information is received from the aircraft. A number of times that an abnormal switching occurred for the pumps within a window of consecutive flights is determined by the computer system when the abnormal switching is identified from the flight information. A set of actions is performed by the compute system when the abnormal switching occurred a number of times for the pumps within the window of consecutive flights that exceeds a set of thresholds for the abnormal switching that is considered healthy for the pumps.

The jet engine comprising a ramjet air path extending from an intake, into a combustion chamber, and out an exhaust nozzle, a fuel inlet leading into the combustion chamber, an oxidizer inlet leading into the combustion chamber and a partition being operable to selectively close the ramjet air path upstream of the combustion chamber to allow operation of the jet engine in rocket mode and open the ramjet air path to allow operation of the jet engine in ramjet mode.

An emergency wind turbine system for an aircraft including an outer structure in which an opening is made includes an emergency wind turbine including: a mast; a turbine including a body mounted on the mast that rotates about an axis of rotation, and a single blade or two blades extending radially from the body between a blade root and a blade head; a locking device to lock rotation of the turbine body about the axis of rotation, when the emergency wind turbine moves between retracted and deployed positions, such that the blade root axis forms an acute locking angle with an orthogonal projection of the longitudinal axis of the mast over a plane substantially perpendicular to the axis of rotation of the turbine and in which the blade root axis extends, to reduce the volume swept by the turbine when it moves between the retracted and deployed positions.

A ram air turbine has turbine blades connected to rotate a transmission shaft. The transmission shaft is connected to drive a first gear which is engaged to drive a second gear. The second gear is connected to rotate an output shaft extending through a strut away from the transmission shaft. A governor arrangement is configured to change a pitch angle of the blades in response to speed, and includes counterweights acting on a spring in the governor arrangement. The governor spring is positioned on an opposed side of the strut relative to the turbine.

An emergency wind turbine system for an aircraft including an outer structure in which an opening is made includes an emergency wind turbine including: a mast; a turbine including a body mounted on the mast that rotates about an axis of rotation, and a single blade or two blades extending radially from the body between a blade root and a blade head; a locking device to lock rotation of the turbine body about the axis of rotation, when the emergency wind turbine moves between retracted and deployed positions, such that the blade root axis forms an acute locking angle with an orthogonal projection of the longitudinal axis of the mast over a plane substantially perpendicular to the axis of rotation of the turbine and in which the blade root axis extends, to reduce the volume swept by the turbine when it moves between the retracted and deployed positions.

A ram air turbine has turbine blades connected to rotate a transmission shaft. The transmission shaft is connected to drive a first gear which is engaged to drive a second gear. The second gear is connected to rotate an output shaft extending through a strut away from the transmission shaft. A governor arrangement is configured to change a pitch angle of the blades in response to speed, and includes counterweights acting on a spring in the governor arrangement. The governor spring is positioned on an opposed side of the strut relative to the turbine.

An auxiliary power unit system of an aircraft includes an auxiliary power unit (APU), a cooling unit for the APU including a heat exchanger, an air inlet in communication with the APU and/or with the cooling unit, an air inlet door unit located at the air inlet, a first duct configured to draw air into the APU and having an entrance in communication with the air inlet, a second duct having an entrance in communication with the air inlet, the heat exchanger being at least partially located within the second duct, an air turbine located within the second duct downstream of the heat exchanger, and an electrical generator coupled to the air turbine.