An aircraft includes a fuselage defining a cabin region and a crown region. The aircraft also includes a duct disposed within the fuselage. The duct is coupled to one or more drying air vents disposed in the crown region and coupled to one or more cabin vents disposed with the cabin region. The one or more drying air vents are configured to output drying air, received via the duct, into the crown region, and the one or more cabin vents are configured to output conditioned air, received via the duct, into the cabin region. The aircraft further includes one or more valves coupled to the duct and configured to, in a first valve position, route airflow within the duct to the one or more drying air vents and configured to, in a second valve position, route the airflow within the duct to the one or more cabin vents.

A cabin air control system for an aircraft comprising a plurality of compressed air sources, each operable to provide compressed air, at least one air outlet, a conduit system connected to the air sources and the air outlet and arranged to conduct air from the air sources downstream to the air outlet, and a plurality of particulate matter detectors configured to detect the presence of particulate matter in air from the air sources. Each detector is associated with a different predefined subset of the air sources by being arranged in the conduit system at a location from which it is only possible to reach the associated subset of the air sources when traversing the conduit system from the respective location towards the air sources in an upstream direction. Any two subsets of the different subsets associated with the different particulate matter detectors include different ones of the air sources.

An architecture for supplying air to a high-pressure compressor (140) of an auxiliary gas generator (14) from a pressurized cabin (12) of an aircraft, comprising: a load compressor (16, 52) rotationally driven by a common rotation shaft (146) providing a mechanical coupling between the high-pressure compressor and a high-pressure turbine (144) of the auxiliary gas generator and supplied by an outside air intake (18, 58); a first regulation valve (22) assembled at the outlet of the load compressor to control all or part of the air flow delivered by the load compressor; a second regulation valve (22) assembled at the outlet of the pressurized cabin to control the air flow drawn from inside the pressurized cabin; a mixer (24) receiving the outputs of the first and second regulation valves to add the air drawn from inside the pressurized cabin to all or part of the air delivered by the load compressor; and a third regulation valve (26) assembled at the outlet of the mixer to control the air flow injected into the high-pressure compressor of the auxiliary gas generator.

There is disclosed a cooling system for a liquid cooled internal combustion aircraft power plant for an aircraft having a tail cone. The cooling system has: an air inlet defined through a wall of the tail cone and fluidly connected to an environment outside the aircraft; a heat exchanger having at least one first conduit fluidly connected to the environment via the air inlet and at least one second conduit in heat exchange relationship with the at least one first conduit and fluidly connectable to a coolant circuitry of the liquid cooled internal combustion aircraft power plant; a blower fluidly connected to the environment via the air inlet; and an air outlet fluidly connected to the blower and defined through a wall of the aircraft upstream of the air inlet relative to a direction of an airflow along the aircraft.

An environmental control system of an aircraft includes a compressing device including a compressor and a turbine configured to receive a flow of first medium sequentially. The compressing device additionally includes a second turbine configured to receive a flow of second medium distinct from the first medium. A dehumidification system is arranged in fluid communication with the turbine and a bypass valve is configured to divert the flow of the first medium output from the compressor around the turbine.

An environmental control system of an aircraft includes a compressing device including a compressor and a turbine configured to receive a flow of first medium sequentially and a second turbine arranged in fluid communication with an outlet of the compressor. The second turbine is configured to receive a flow of second medium distinct from the first medium. A dehumidification system is arranged in fluid communication with the turbine, a first bypass valve is configured to divert at least a portion of the flow of the first medium output from the compressor around the turbine, and a second bypass valve configured to divert at least a portion of the flow of first medium output from the compressor to the second turbine.

An integrated multimode thermal energy transfer system, method and apparatus for full-scale clean fuel electric-powered multirotor aircraft with automatic on-board-capability to provide sensor-based temperature awareness and adjustment to critical components and zones of the aircraft. Automatic computer monitoring, including by a programmed triple-redundant digital autopilot computer, controls each motor-controller and motor to produce pitch, bank, yaw and elevation, while simultaneously measuring, calculating, and adjusting temperature and heat transfer of aircraft components and zones, to protect critical components from exceeding operating parameters and to provide a safe, comfortable environment for occupants during flight. By using the results of the measurements to inform computer monitoring, the methods and systems can use byproducts including thermal energy disparities and differentials related to both fuel supply systems and power generating systems to both add and remove heat from different aircraft zones to improve aircraft function, comfort, and efficiency.

An auxiliary power unit (APU) for aircraft is provided. The APU includes one or more battery modules for storing electrical power and an integrated controller adapted to operate the one or more battery modules for electrically powering aircraft subsystems for preflight readiness. A remote interface is communicatively coupled with the integrated controller and is adapted for displaying data from the APU and for receiving user instructions for transmission to the integrated controller for governing flow of electrical current between the APU and the aircraft subsystems.

There is disclosed a cooling system for a liquid cooled internal combustion aircraft power plant for an aircraft having a tail cone. The cooling system has: an air inlet defined through a wall of the tail cone and fluidly connected to an environment outside the aircraft; a heat exchanger having at least one first conduit fluidly connected to the environment via the air inlet and at least one second conduit in heat exchange relationship with the at least one first conduit and fluidly connectable to a coolant circuitry of the liquid cooled internal combustion aircraft power plant; a blower fluidly connected to the environment via the air inlet; and an air outlet fluidly connected to the blower and defined through a wall of the aircraft upstream of the air inlet relative to a direction of an airflow along the aircraft.

A system that allows using a fuel cell air compressor for cabin pressurization, cabin heat, and wing de-icing. One of the fuel cell's primary components, the compressor produces the pressure necessary to operate. The operating pressure is much higher than necessary for cabin pressurization so bleed air can be used for this purpose. Compressing air requires a lot of energy, and much of that energy is transferred into the air being compressed. This warm, compressed air could then be used to heat up the passenger cabin. Similarly the warm compressed air produced from the fuel cell compressor can be used to inflate the pouches on the leading edges of the wings to remove ice in the event of extreme weather. A control system is provided to operate each individual system. These systems will require control over multiple lines and valves, and will be registering feedback from pressure sensors mounted at each point. The onboard computer system will monitor user inputs and control outputs corresponding to each system.