Abstract: A cooling system for use with a power electronics assembly comprising an array of line-replaceable units is provided. The cooling system includes a first manifold coupled in flow communication with the array of line-replaceable units, and a fluid supply coupled in flow communication with the first manifold. The fluid supply is configured to channel cooling fluid towards the first manifold such that the cooling fluid is discharged towards the line-replaceable units in the array substantially simultaneously.

Abstract: An aircraft including an airframe, a propulsion system, and a heat exchanger is presented. The heat exchanger of the aircraft may include (i) a structural body including a plurality of hollow channels, (ii) a first fluid positioned within the plurality of hollow channels of the structural body, (iii) a plurality of openings positioned on a first side of the structural body and in fluid communication with the plurality of hollow channels, (iv) a wick structure positioned on the first side of the structural body, and further positioned adjacent to an exterior of the plurality of hollow channels and in fluid communication with the plurality of openings, (v) an inlet to the structural body operable to provide a second fluid from an aircraft system, and (vi) an outlet from the structural body operable to receive the second fluid after receiving heat from the first fluid.

Abstract: A microtruss structure includes a first plane having a first plurality of unit cells. Each of the first plurality of unit cells includes a first plurality of struts and a first node connecting three or fewer struts of the first plurality of struts such that each strut of the first plurality of struts extends through the first node. The microtruss structure also includes a second plane having a second plurality of unit cells. Each of the second plurality of unit cells includes a second plurality of struts and a second node connecting three or fewer struts of the second plurality of struts such that each strut of the second plurality of struts extends through the second node.

Abstract: In one aspect, conduction cooled modules are described herein. In some implementations, a conduction cooled module comprises first and second external support structures arranged in facing opposition to one another, forming a component envelope therebetween. In some implementations, the modules are configured to contact at least one cold plate and to retain at least one printed wiring board in the component envelope in between the first external support structure and the second external support structure.

Abstract: An aircraft including an airframe, a propulsion system, and a heat exchanger is presented. The heat exchanger of the aircraft may include (i) a structural body including a plurality of hollow channels, (ii) a first fluid positioned within the plurality of hollow channels of the structural body, (iii) a plurality of openings positioned on a first side of the structural body and in fluid communication with the plurality of hollow channels, (iv) a wick structure positioned on the first side of the structural body, wherein the wick structure is positioned adjacent to an exterior of the plurality of hollow channels and in fluid communication with the plurality of openings, (v) an inlet to the structural body operable to provide a second fluid from an aircraft system, and (vi) an outlet from the structural body operable to receive the second fluid after receiving heat from the first fluid.

Abstract: A cooling system for use with a power electronics assembly comprising an array of line-replaceable units is provided. The cooling system includes a first manifold coupled in flow communication with the array of line-replaceable units, and a fluid supply coupled in flow communication with the first manifold. The fluid supply is configured to channel cooling fluid towards the first manifold such that the cooling fluid is discharged towards the line-replaceable units in the array substantially simultaneously.

Abstract: A microtruss structure includes a first plane having a first plurality of unit cells. Each of the first plurality of unit cells includes a first plurality of struts and a first node connecting three or fewer struts of the first plurality of struts such that each strut of the first plurality of struts extends through the first node. The microtruss structure also includes a second plane having a second plurality of unit cells. Each of the second plurality of unit cells includes a second plurality of struts and a second node connecting three or fewer struts of the second plurality of struts such that each strut of the second plurality of struts extends through the second node.

Abstract: In one aspect, conduction cooled modules are described herein. In some implementations, a conduction cooled module comprises first and second external support structures arranged in facing opposition to one another, forming a component envelope therebetween. In some implementations, the modules are configured to contact at least one cold plate and to retain at least one printed wiring board in the component envelope in between the first external support structure and the second external support structure.

Abstract: An aircraft fuselage sidewall may include an aircraft sidewall volume and a flow controller. The aircraft sidewall volume may be delineated by an aircraft skin forming an outboard boundary of the aircraft sidewall volume, a passenger cabin sidewall forming an inboard boundary of the aircraft sidewall volume and fuselage frame structures forming axial boundaries of the aircraft sidewall volume. The flow controller may be positioned at a portion of the aircraft sidewall volume to selectably control air flow through the aircraft sidewall volume.

Abstract: An aircraft micro-lattice cross-flow heat exchanger and methods are presented. A first aircraft fluid source inlet provides a first fluid from a first aircraft system, and a second aircraft fluid source inlet provides a second fluid from a second aircraft system. A structural body supports aviation induced structural loads and exchanges heat between the first fluid and the second fluid. The structural body comprises hollow channels forming two interpenetrating fluidically isolated volumes that flow the first fluid within the hollow channels and flow the second fluid external to the hollow channels isolated from the first fluid. The hollow channels comprise a hollow three-dimensional micro-truss comprising hollow truss elements extending along at least three directions, and hollow nodes interpenetrated by the hollow truss elements.

Abstract: An aircraft fuselage sidewall may include an aircraft sidewall volume and a flow controller. The aircraft sidewall volume may be delineated by an aircraft skin forming an outboard boundary of the aircraft sidewall volume, a passenger cabin sidewall forming an inboard boundary of the aircraft sidewall volume and fuselage frame structures forming axial boundaries of the aircraft sidewall volume. The flow controller may be positioned at a portion of the aircraft sidewall volume to selectably control air flow through the aircraft sidewall volume.

Abstract: A forward in flight entertainment system (IFE) which allows air to be directed to and exhausted from the IFE equipment in isolation from the cabin conditioned air. Further, potential IFE generated smoke may be kept isolated from the cabin air. The forward IFE equipment is located in forward sections of the aircraft system switching from ground to air mode is accomplished through air/ground signal 10 responsive to landing gear truck tilt. Once the air/ground transition from ground mode to air mode has occurred, ventilation valves 1 and 2 will be closed and the heated air will be exhausted overboard by forward IFE cooling overboard valve 4 whose overboard flow increases with altitude and cabin to ambient pressure differential.

Abstract: An aft in flight entertainment system “IFE” which allows air to be directed to and exhausted from the IFE equipment in isolation from the cabin conditioned air. Further potential IFE generated smoke may be kept isolated from the cabin air. The aft IFE equipment is located in the rear sections of the aircraft. Valves controlling air flow are responsive to input signals. A fan draws cooling air through a video control cabinet through a duct which splits into an overhead branch and an inboard branch.

Abstract: An aft in flight entertainment system (IFE) which allows air to be directed to and exhausted from the (IFE) equipment in isolation from the cabin conditioned air. Further potential (IFE) generated smoke may be kept isolated from the cabin air. The aft (IFE) equipment is located in the rear sections of the aircraft.

Abstract: A forward in flight entertainment system (IFE) which allows air to be directed to and exhausted from the (IFE) equipment in isolation from the cabin conditioned air. Further, potential IFE generated smoke may be kept isolated from the cabin air. The forward IFE equipment is located in forward sections of the aircraft.