An example auxiliary power unit bracket includes, among other things, a gearbox mounting face and a compartment mounting face, the gearbox mounting face configured to attach to an auxiliary power unit gearbox below a sump level line, the compartment mounting face configured to attach to a portion of an auxiliary power unit compartment above the sump level line.

An apparatus for unlocking an actuator, such as a RAT actuator includes a first member; and a second member movable between a blocking position in which said second member is engaged with said first member so as to block movement of said first member and an unblocking position in which said second member is disengaged from said first member so that movement of the first member is not blocked. The first member is an arm arranged such that in the blocking position it is disposed between said second member and a lock release element of said actuator.

A method of cooling an auxiliary power unit (APU) of an aircraft having prime mover engines fed with aircraft fuel, comprises: using the aircraft fuel as a heat sink to absorb the heat generated by the APU.

This invention comprises a control device and a communication port device applied to drone, and a drone using such devices. The control device comprises a carrier board and a main control board that is detachably configured on the carrier board, said main control board is electrically connected with the carrier board, and the carrier board is configured with an interface device in which connections between a plurality of kinds of external devices with said carrier board are established. The carrier board is mainly used for connection with other external electronic devices and power distribution, and the main control board is responsible for processing sensor data and delivering control information. The main control board and the carrier board are connected through a single interface to enable a data transmission. The communication port device is configured on the drone flight controller.

Aspects of this disclosure relate to externally accessible auxiliary power unit (APU) pump assembly, comprising: a pump configured to pressurize an accumulator that is used to start an APU of an aircraft; a pressure gauge for the accumulator; and a support frame configured to be mounted within an outer wall of the aircraft, wherein the support frame defines an externally accessible compartment and secures the pump and the pressure gauge within the externally accessible compartment.

This invention concerns an aircraft propulsion system in which an engine has an engine core comprising a compressor, a combustor and a turbine driven by a flow of combustion products of the combustor. At least one propulsive fan generates a mass flow of air to propel the aircraft. An electrical energy store is provided on board the aircraft. At least one electric motor is arranged to drive the propulsive fan and the engine core compressor. A controller controls the at least one electric motor to mitigate the creation of a contrail caused by the engine combustion products by altering the ratio of the mass flow of air by the propulsive fan to the flow of combustion products of the combustor. The at least one electric motor is controlled so as to selectively drive both the propulsive fan and engine core compressor.

Integrated arrangements of electrical machines and power electronics converters are described. One such arrangement comprises: an electrical machine comprising one or more windings; a power electronics converter arranged to supply current to or receive current from the one or more windings of the electrical machine; a magnetocaloric effect (MCE) material in thermal contact with the power electronics converter; and a heat sink for removing heat from the MCE material. The MCE material is arranged in proximity to the one or more windings of the electrical machine whereby, in use, stray magnetic flux from the windings of the electrical machine passes through the MCE material and activates the MCE material. The repeated application and removal of the stray flux during normal operation of the electrical machine creates cycles of magnetic refrigeration, which removes heat from the power electronics converter.

An aircraft includes a fuselage, a main entry door with an associated passenger loading zone, an auxiliary power unit (APU) in the fuselage, and an APU inlet assembly. The APU inlet assembly has an inlet duct, and inlet door, and means for redirecting sound waves coupled to or integrated with an interior side of the inlet door. The inlet duct has a first end coupled to the APU, and a second end associated with the inlet door. The inlet door moves between a closed position and an open position. The means for redirecting sound waves is positioned at a particular location on the interior side of the inlet door, and includes certain acoustic features and characteristics. The particular location and the acoustic features and characteristics cooperate to redirect sound waves generated by the APU away from the passenger loading zone when the inlet door is in the open position.

The disclosure describes a system that includes an auxiliary power unit (APU), an APU throttle valve, and an environmental control system (ECS) bypass valve. The APU is configured to receive cabin discharge air from an aircraft cabin and receive ECS supply air from an air pressurization system (APS). The APU throttle valve is configured to control flow of cabin discharge air from the cabin to the APU. The ECS bypass valve configured to control flow of ECS supply air from the APS to the APU.

A gas turbine engine for an aircraft includes a compressor, a combustion chamber, and a turbine having at least one stator, and at least one rotor. Each stator and rotor is formed by a plurality of blades, a fluid channel is formed between two consecutive blades, and each blade has two opposing surfaces. The compressor is in fluid communication with a first group of stator channels, and the combustion chamber is in fluid communication with a second group of stator channels, such that heat exchange can be performed through two opposing surfaces of at least one stator blade. The outer and the inner walls define a duct for the passage of the heated fluid through the rotor blades, and the outer wall is also arranged for directing the compressed air towards the combustion chamber.