Abstract: A radar device is provided. The radar device includes an antenna and a housing having an exterior wall. The radar device also includes an electronics module having a heat source contained within the housing. Additionally, the radar device includes a heat pipe having a first end and a second end. The first end is positioned proximate to the heat source, and the heat pipe is configured to transfer heat from the first end of the heat pipe to the second end of the heat pipe to reduce an amount of heat at the heat source. The heat pipe may be an evaporator-condenser heat pipe. The second end of the heat pipe may be positioned proximate to a first dissipating feature. The heat source may be a power amplifier, waveguide assembly, printed circuit board, or other electronics, and the first dissipating feature may be the exterior wall of the housing.

Abstract: The cabin conditioning system can include a cabin air loop, a refrigerant loop, and a set of thermal rejection components. The system can optionally include a phase-change fluid loop. However, the cabin conditioning system can additionally or alternatively include any other suitable set of components. The cabin conditioning system functions to condition a cabin interior (and/or an air volume therein) of a vehicle, such as an atmospheric and/or space-flight capsule. Additionally or alternatively, the system can function to reject heat from the vehicle interior and/or vehicle power systems (e.g., avionics components thereof). Additionally or alternatively, the system can function to maintain the humidity of air within the cabin interior. However, the cabin conditioning system can include any other suitable components.

Abstract: The invention relates to a heat exchanger for heating gas to a temperature in the range from 150 to 400° C., wherein the gas is heated by indirect heat transfer and all the surfaces of the walls of the heat exchanger which come into contact with the gas have been hot dip galvanized and the surfaces which come into contact with the gas, after the hot dip galvanization, have been heat treated at a temperature in the range from 400 to 750° C. The invention further relates to the use of the heat exchanger.

Abstract: An example temperature sensing device includes an air distribution inlet through which primary air is blown into via an environmental control system, a cabin air inlet through which secondary air enters from a passenger area of a fuselage and the cabin air inlet is coupled to the air distribution inlet through a duct and the secondary air is passively drawn into the cabin air inlet and to the duct due to a pressure difference present in the duct, and a temperature sensor coupled to the duct and positioned downstream of the cabin air inlet along an airflow path of the secondary air so as to be exposed to the secondary air drawn in through the cabin air inlet and flowing through the duct.

Abstract: An environmental control system of a vehicle includes a first compression device including a compressor, a first turbine, and a power turbine operably coupled by a shaft. The first turbine is configured to receive a first medium, the compressor is configured to receive a second medium, and the power turbine is configured to receive a third medium. A second compression device, separate from the first compression device, includes a second turbine. The environmental control system is operable in a first mode and a second mode. In the first mode, the second medium is provided to the compressor and the second turbine sequentially. In the second mode, the second medium bypasses the second turbine. In in both the first mode and the second mode, only the second medium is provided to an outlet of the environmental control system.

Abstract: Thermoelectric cooling assemblies, and systems and methods employing such assemblies integrated within an aircraft antennae radome, with the cooling assemblies operating exclusively via electrical power provided by scavenging waste heat from an adjoining antennae array provide thermal protection to heat-sensitive structural components adjoining the antennae array.

Abstract: A thermal component has a shield portion and a heat exchanger portion. The shield portion includes a plurality of cells adapted to inhibit radio radiation (RF) having a frequency within a target frequency range, while the heat exchanger portion includes a plurality of elongated channels, each one of the elongated channels being physically connected to and in fluid communication with at least one corresponding cell of the plurality of cells.

Abstract: Some embodiments include a thermal ground plane comprising a first and second casing with folding and non-folding regions. The thermal ground plane may also include a vapor structure and a mesh. The mesh may be disposed on an interior surface of the second casing and the mesh include a plurality of arteries extending substantially parallel with a length of the thermal ground plane. The folding region of the first casing may have an out-of-plane wavy structure. The valleys and peaks of the out-of-plane wavy structure, for example, may extend across a width of the first active region substantially parallel with a width of the thermal ground plane.

Abstract: A vibrorotational fluid flow actuator includes: a first vibrorotational component comprising a first body including an axis, a plurality of first legs extending from a bottom surface of first body in a direction of and at an angle to the axis, and a plurality of first blades extending from a respective side of the first body in a direction perpendicular to the axis, wherein when the first vibrorotational component is placed on a chassis, vibration of the chassis induces rotation of the body such that the blades and body rotate about the axis of the body thereby inducing fluid flow in a fluid surrounding the actuator.

Abstract: An air conditioner indoor unit includes a body including an air outlet, an outer air deflector located at the air outlet and configured to open and close the air outlet, and an inner air deflector located at an inner side of the outer air deflector and configured to expose and cover at least part of the outer air deflector. The outer air deflector includes a plurality of vent holes penetrating the outer air deflector along a thickness direction of the outer air deflector.

Abstract: An air conditioning pack management system for controlling distribution of a predetermined amount of conditioned air from a system comprising two or more air conditioning packs, the pack management system comprising a management unit arranged to proportion the predetermined amount of conditioned air to be provided by one or more of the two or more packs based on the respective operating efficiencies of the packs or other pre-selected metrics.

Abstract: Disclosed is a cabin air compressor (CAC) of an aircraft environmental control system, the CAC having: a CAC case defining a forward end and an aft end axially spaced apart axially from the forward end, wherein the forward end defines a compressor inlet; and a supplemental cooling passage defined by the CAC case, wherein the supplemental cooling passage is configured to direct a supplemental cooling medium through it.

Abstract: A heat exchanger is provided that can include furcating unit cells coupled with each other. Each of the unit cells can be elongated along an axis and include a sidewall that defines annular ring openings on opposite ends of the unit cell along the axis. The sidewall also can define undulating annular rings between the annular ring openings and axially separated from each other along the axis. The sidewall can further define angled openings into the unit cell both above and below each of the undulating annular rings. At least a first opening of the annular ring openings and the angled openings can be configured to be an inlet to receive a first fluid into the unit cell and at least a second opening of the annular ring openings and the angled openings configured to be an outlet through which the first fluid exits the unit cell.

Abstract: An apparatus includes first and second microchannel heat exchangers and first and second pipes. The first heat exchanger includes a first inlet, a second inlet, a first tube, a second tube, a first outlet, and a second outlet. Refrigerant at the first inlet is directed through the first tube to the first outlet and the first pipe. Refrigerant at the second inlet is directed through the second tube to the second outlet and the second pipe. The second heat exchanger includes a third inlet, a fourth inlet, a third tube, a fourth tube, a third outlet, and a fourth outlet. The third inlet directs refrigerant from the first pipe through the third tube towards the third outlet. The fourth inlet directs the refrigerant from the second pipe through the fourth tube towards the fourth outlet. The first pipe overlaps the second pipe between the two heat exchangers.

Abstract: A method for performance determination of a heat pipe with an arbitrary liquid flow area and prescribed geometric dimensions, an external and internal structure, a heat pipe material and a working fluid, heating and cooling surface areas, and condenser cooling conditions is provided to obtain operating and performance parameters, wherein the operating and performance parameters are temperature distribution within the heat pipe, a heat transferred via a phase change and a conduction, an axial variation of a radius of curvature of a liquid-vapor interface along the heat pipe, a vapor temperature and pressure of the working fluid, by simulating a flow and an energy transfer inside.

Abstract: A heat exchanger having an integrated support structure particularly suited for thermal management of heat generating components such as battery thermal management applications or thermal management of other electronic components is disclosed. The heat exchanger includes a top plate and a base tray defining a plurality of fluid channels that extend between an inlet manifold area and an outlet manifold area. The top plate has a first side defining a primary heat transfer area and a second side for effecting a sealing relationship between the top plate and the base tray. In some instances, the top plate includes a thermally conductive material while the base tray includes a non-thermally conductive material. In some instances the base tray cooperates with a cover portion to define an enclosure for housing the heat generating components.

Abstract: A heat dissipation structure has a heat dissipation base and at least one heat conduction assembly mounted in a through hole of the heat dissipation base. Each of the at least one heat conduction assembly includes a resilient clamp and a heat pipe. When a transceiver is inserted in the through hole of the heat dissipation base, two heat conducting sections of the heat pipe are pushed by the resilient clamp to abut against the transceiver and the heat dissipation base respectively. Heat generated while the transceiver is operating can be quickly and efficiently conducted through the heat pipe to the heat dissipation base and then dissipated. Temperature increase of the transceiver can be effectively avoided and performance and reliability of the transceiver during operation can be ensured.

Abstract: The present application discloses two-phase cooling devices that may include at least three substrates: a metal with a wicking structure, an intermediate substrate and a backplane. A fluid may be contained within the wicking structure and vapor chamber for transporting thermal energy from one region of the thermal ground plane to another region of the thermal ground plane, wherein the fluid may be driven by capillary forces within the wicking structure. The intermediate substrate may form narrow channels within the wicking structure, providing high capillary forces to support large pressure differences between the liquid and vapor phases, while minimizing viscous losses of the liquid flowing in the wicking structure.

Abstract: A thermal conductor includes a plurality of thermal conducting portions; and joint portions made of a material having flexibility and configured to join the respective thermal conducting portions with each other, having voids where neither the thermal conducting portion nor the joint portion is present, and satisfying a condition of 0.5?[(S1?S0)/S0]×100?20 when an area of the thermal conductor in a planar view in a first direction is expressed by S0 [cm2] and an area of the thermal conductor in the planar view in the first direction in a pressed state that the thermal conductor is pressed by 0.2 MPa in the first direction is expressed by S1 [cm2]. Accordingly, the thermal conductor satisfies both ensuring adhesiveness to a member in contact with the thermal conductor in use and suppressing excessive deformation of the thermal conductor in a compressed state.

Abstract: 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.