A primary structural assembly for an aircraft outside-skin heat exchanger, the assembly comprising an outer-skin portion which defines an outer shape of the aircraft and forms a portion of a hull of the aircraft, wherein the outer-skin portion comprises at least one recess, a thermal-transfer fluid connection which is designed to convey a thermal-transfer fluid into the recess, a component which closes the recess, and at least one retaining element which is arranged in or on the recess and is configured to hold the component closing the recess, in the recess. Further, an aircraft including such a primary structural assembly and a method for attaching the aircraft outside-skin heat exchanger are disclosed.

A counterflow heat exchanger configured to exchange heat between a first fluid flow at a first pressure and a second fluid flow at a second pressure includes a first fluid inlet, a first fluid outlet fluidly coupled to the first fluid inlet via a core section, a second fluid inlet, and a second fluid outlet fluidly coupled to the second fluid inlet via the core section. The core section includes a plurality of first fluid passages configured to convey the first fluid flow from the first fluid inlet toward the first fluid outlet, and a plurality of second fluid passages configured to convey the second fluid flow from the second fluid inlet toward the second fluid outlet such that the first fluid flow exchanges thermal energy with the second fluid flow at the core section. Each first fluid passage of the plurality of first fluid passages has a circular cross-section.

A ram air module for use in a ram air system, the ram air module includes a diffuser having a diffuser body including an inlet end and an outlet end, a flow diverter assembly connected to the inlet end of the diffuser body, and a valve connected to the outlet end of the diffuser body.

Electro oxidation membrane evaporator 1 comprises sweep air handler 60; fluid tank 20 defining a fluid container; fluid contactor/separator 30; oxidation cell 40; and scrubber 80. Electro oxidation membrane evaporator 1 may allow higher percent water recovery from wastewater prior to delivering brine to a brine water recovery system and can allow O.sub.2 from air such as cabin air to continuously diffuse into the wastewater as O.sub.2 is consumed to generate oxidants, helping to eliminate the low oxidant environment at the end of the cycle that causes pH to remain high, and low pH prevents precipitates from forming for longer so more water can be evaporated from the wastewater.

Electro oxidation membrane evaporator 1 comprises sweep air handler 60; fluid tank 20 defining a fluid container; fluid contactor/separator 30; oxidation cell 40; and scrubber 80. Electro oxidation membrane evaporator 1 may allow higher percent water recovery from wastewater prior to delivering brine to a brine water recovery system and can allow O.sub.2 from air such as cabin air to continuously diffuse into the wastewater as O.sub.2 is consumed to generate oxidants, helping to eliminate the low oxidant environment at the end of the cycle that causes pH to remain high, and low pH prevents precipitates from forming for longer so more water can be evaporated from the wastewater.

A system for manufacturing a kitchen arrangement for a cabin of a vehicle includes a primary module with an electrical energy supply device, a cooling device, and at least one supply connection for supplying the primary module with a requisite. The system also includes at least one auxiliary module that is couplable with the primary module. The cooling device is set up to provide a stream of cooled fluid to a fluid outlet. At least one outer boundary surface of the primary module comprises an electrical connection coupled with the electrical energy supply device and a fluid connection coupled with the fluid outlet. The at least one outer boundary surface is adjusted for coupling with an auxiliary module having a correspondingly shaped boundary surface.

In some examples, an air treatment system includes a filter, an ozone sensor, and a separator configured to separate air into a nitrogen-enriched gas and an oxygen-enriched gas. The filter is configured to remove ozone from an air stream and supply filtered air to the separator. The ozone sensor is configured to sense an ozone level of the filtered air issuing from the filter prior to encountering the separator. The air treatment system may include processing circuitry configured to monitor the ozone level sensed. The air treatment system may be part of an inerting system configured to supply the nitrogen-enriched gas to an ullage space of a fuel tank.

In some examples, an air treatment system includes a filter, an ozone sensor, and a separator configured to separate air into a nitrogen-enriched gas and an oxygen-enriched gas. The filter is configured to remove ozone from an air stream and supply filtered air to the separator. The ozone sensor is configured to sense an ozone level of the filtered air issuing from the filter prior to encountering the separator. The air treatment system may include processing circuitry configured to monitor the ozone level sensed. The air treatment system may be part of an inerting system configured to supply the nitrogen-enriched gas to an ullage space of a fuel tank.

A hypersonic aircraft includes one or more leading edge assemblies that are designed to cool the leading edge of certain portions of the hypersonic aircraft that are exposed to high thermal loads, such as extremely high temperatures and/or thermal gradients. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. A coolant supply may be in fluid communication with at least one fluid passageway that passes through the outer wall to deliver a flow of cooling fluid to the stagnation point. In addition, a nose cover is positioned at least partially over or within the at least one fluid passageway and is formed from a material that ablates or melts when the leading edge is exposed to a predetermined critical temperature, the nose cover being configured for restricting the flow of coolant until the nose cover is ablated or melted away.

An aircraft environmental control system includes a bleed air input and a RAM air input, heat exchanger means for receiving bleed air from the bleed air input and RAM air from the RAM air input and using the RAM air to cool the bleed air, and ejector arranged to receive bleed air from the bleed air input at a nozzle shaped to reduce the pressure of the received bleed air such as to create a low pressure area in the ejector. The ejector has a port arranged such that ambient air is drawn into the ejector due to the low pressure area in the ejector. The ambient air is mixed with bleed air to provide mixed air that is further pressurised and conditioned and combined with the cooled bleed air provided to the aircraft.