A vehicle is provided including a structure including a skin defining an outside surface exposed to ambient cooling flow and an inside surface. The structure includes a first structural member extending from the inside surface of the skin and a second structural member extending from the inside surface of the skin; and a thermal management system including a heat exchanger assembly positioned adjacent to, and in thermal communication with, the inside surface of the skin, the heat exchanger assembly positioned at least partially between the first and second structural members of the structure.

A vehicle cabin air temperature controller includes a two-position three-way solenoid valve with one inlet to take in coolant supplied by a pump, a first outlet to supply a cooling leg, and a second outlet to supply a bypass leg. The vehicle cabin air temperature controller also includes a controller to control flow of the coolant via the first outlet and the second outlet of the solenoid valve, and a cabin air heat exchanger to obtain an input coolant based on the control of the flow via the first outlet and the second outlet and to provide cooled cabin air to the vehicle cabin. The control of the flow of the coolant via the first outlet and the second outlet controls a flow rate of the input coolant.

An aircraft propulsion system includes a gas turbine engine; an environmental control system (ECS); and a bleed flowpath from the gas turbine engine through the ECS. A turbine is along the bleed flowpath and a propulsion fan is mechanically coupled to the turbine to be driven by the turbine.

An environmental control system (ECS) for use with a gas turbine engine has an air cycle system (ACS) and a vapor cycle system (VCS). The VCS has along a vapor compression flowpath: a VCS compressor; a heat donor leg of a VCS condenser; an expansion device; and a heat receiving leg of a VCS evaporator. The ACS has along a bleed flowpath: a bleed air inlet; a primary heat exchanger; an ACS compressor; a secondary heat exchanger; a turbine coupled to the ACS compressor to drive the ACS compressor; a heat donor leg of the VCS evaporator; a water collector; and a heat receiving leg of the VCS condenser.

An outer panel-mediated cooling system includes: an outer shell including an outer panel, an inner panel located inward of the outer panel, and a heat-insulating layer located between the outer and inner panels; a cooling chamber that is located between the outer and inner panels and in which a gas releases heat outside through the outer panel and is thus cooled; a circulation loop in which a heat medium circulates, the circulation loop including a heating section located inward of the inner panel to heat the heat medium and a cooling section located in the cooling chamber to cool the heat medium; a flow path-forming structure located in the cooling chamber to form a circulation path for the gas; and a fan located in the cooling chamber to exert a drive force on the gas to allow the gas to circulate in the circulation path.

A gas turbine engine includes a compressor section and a turbine section operably coupled to the compressor section. The gas turbine engine further includes a means for selectively releasing a cooling fluid flow produced at a cryogenic temperature and a plumbing system in fluid communication with the means for selectively releasing the cooling fluid flow. The plumbing system is configured to route the cooling fluid flow to one or more of the compressor section and the turbine section.

An environmental control system (ECS) of an aircraft includes an inlet for a first medium, an outlet for the first medium, an air cycle machine including a compressor, a turbine, and a shaft operably coupling the compressor and the turbine, and a plurality of heat exchangers arranged in fluid communication with the air cycle machine. A first heat exchanger of the plurality of heat exchangers is arranged directly downstream from the turbine and heat is transferred to the first medium within the first heat exchanger. A water extractor is arranged directly downstream from the first heat exchanger and a flow path connects the air cycle machine, the plurality of heat exchangers, and the water extractor with the inlet and the outlet.

An aircraft with a thermal management system and method of operating the thermal management system within an aircraft includes an avionics unit adapted to store at least one heat generating component, a first interface operably coupled to the avionics unit and thermally coupled to the at least one heat generating component; and a plurality of heat pipes, wherein a first end of the plurality of heat pipes is coupled to the first interface, defining a hot interface, and a second end of the heat pipes is coupled to the at least one of the fuselage, the wing, the skin, or the support structure.

A system includes a power cycle and a cooling cycle. The power cycle includes a first compressor, a recuperative heat exchanger, a waste-heat heat exchanger, and a turbine. The turbine includes a drive shaft coupled to the first compressor. The working fluid from the waste-heat heat exchanger drives the turbine, the drive shaft, and the first compressor. The recuperative heat exchanger cools the working fluid from the turbine, and at least one ram-air heat exchanger further cools the working fluid from the recuperative heat exchanger. The first compressor is configured to pressurize the working fluid from the at least one ram-air heat exchanger. The cooling cycle includes a pump, an isenthalpic valve, an ambient air heat exchanger, and a second compressor. The cooling cycle cools the working fluid and ambient air and is connected to the power cycle in the at least one ram-air heat exchanger.

The system can include an on-board thermal management subsystem. The system 100 can optionally include an off-board (extravehicular) infrastructure subsystem. The on-board thermal management subsystem can include: a battery pack, one or more fluid loops, and an air manifold. The system 100 can additionally or alternatively include any other suitable components.