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 trolley compartment for an on-board kitchen intended for installation in a transport vehicle comprises a frontal access aperture as well as a rear wall that lies opposite the access aperture. A worktop forms an upper boundary of the trolley compartment. A first cooling fluid duct, which is connectable to an interior space of the trolley compartment via at least one first cooling fluid aperture, is integrated into or arranged adjacent to the worktop. At least one first removable cooling fluid aperture cover is selectively mountable in the first cooling fluid duct over the first cooling fluid aperture to separate the first cooling fluid duct from the interior space of the trolley compartment, or demountable from the first cooling fluid duct to connect the first cooling fluid duct to the interior space of the trolley compartment via the first cooling fluid aperture.

Commercial supersonic aircraft and associated systems and methods. A representative commercial supersonic aircraft includes a fuselage configured to carry a crew and between 20 and 60 passengers, a delta wing mounted to the fuselage, and a propulsion system carried by at least one of the wing and the fuselage, the propulsion system including a plurality of engines, at least one variable-geometry inlet, and at least one variable-geometry nozzle.

Disclosed is a method and a device for thermally controlling a plurality of cabins of a vehicle from a mixing chamber supplied with air from at least one air supply device of which at least the temperature is controlled, each cabin being supplied with air by a supply conduit specific to this cabin. At least one cabin is supplied with air at a temperature adjusted by at least one individual exchanger associated with the supply conduit specific to this cabin, in which a second circuit is supplied with a heat transfer fluid from at least one heat transfer fluid thermal regulation loop of the vehicle. Also disclosed is a vehicle provided with at least one thermal control device.

A cooling system for a galley installed in a transportation device, in particular an aircraft, has a cooling device with a coolant circuit configured to have a coolant flow therethrough. A fluid line is configured to have a fluid to be cooled flow therethrough and is thermally coupled with the coolant circuit to transfer heat from the fluid to be cooled to the coolant circulating in the coolant circuit, and an air line configured to be flowed through with air and thermally coupled to the coolant circuit of the cooling device to transfer heat from the coolant to the air line. The air line, downstream of the thermal coupling of the air line with the coolant circuit, is connectable to a cabin region of the transportation device accommodating the galley to supply the cabin region with air warmed by heat transfer from the coolant circulating in the coolant circuit.

An Environmental Control Systems (ECS) for an aerospace vehicle comprises an air supply airflow path inputting, monitoring, and conditioning air from external to the vehicle, and a recirculation airflow path inputting, monitoring, filtering, and moving air from one portion of the interior of the vehicle to another portion. The air supply airflow can include a dynamically controlled VOC/ozone converter, which can be operated when the aerospace vehicle is on the ground. The recirculation airflow path can include a dynamically controlled regenerative gas contaminant filter and/or VOC/CO2 removal device. The filter/adsorption media of the controlled regenerative gas contaminant filter and/or VOC/CO2 removal device can be regenerated by suppling hot air or a vacuum, and gaseous contaminants can be broken down for removal from the regenerative gas contaminant filter by controlling UV irradiation. The controller can alert a flight crew if air quality falls outside predetermined or programmable parameters.

Systems and methods provide airflow to a first area from a second area within a vehicle. The system includes a fan mounted within a door separating the first area from the second area. The fan is configured to direct airflow from the second area into the first area. The fan having a shield positioned adjacent to the second area that is configured to conceal the fan.

The invention relates to a cabin air inlet module (16). The cabin air inlet module (16) comprises a streaming channel body (8). The streaming channel body (8) comprises at least one wall which limits a streaming channel wherein incoming air (5) is supplied to a zone (2) of a cabin (3). The cabin air inlet module (16) comprises an electric heating element (9) which is used for heating the incoming air (5). According to the invention it is proposed that the electric heating element (9) is embodied as a two-dimensional heating element (in particular as a heating paper, a heating web, a heating foil or a heating varnish). The two-dimensional heating element extends along a wall of the streaming channel body (8). The inventive cabin air inlet module (16) is arranged upstream with a small distance (25) from an inlet opening (6) into the zone (2) of the cabin (3). The inventive cabin air inlet module (16) is used for a tempering zones (2) of a cabin (3) of an airplane according to the needs.

Systems and methods for limiting infiltration of cabin air into the flight deck of an aircraft, where the systems include at least one upper nozzle disposed adjacent to and above an outer upper edge of a flight deck doorway and directed downwardly, and at least one lower nozzle disposed adjacent to and below an outer lower edge of the flight deck doorway and directed upwardly; a conduit system to deliver air from a flight deck air supply to the upper and lower nozzles; and an airflow controller configured to provide sufficient air flow from the flight deck air supply to the upper and lower nozzles to create directional airstreams across the gaps between the closed flight deck door and the upper and lower edges of the flight deck doorway, so that the airstreams limit infiltration of cabin air into the flight deck via the gaps.

Systems and methods provide airflow to a flight deck from a passenger entry area. The system includes a fan mounted within a door separating a flight deck from a passenger entry area. The fan is configured to direct airflow from the passenger entry area into the flight deck. The fan having a shield positioned adjacent to the passenger entry area that is configured to conceal the fan.