An air-conditioning duct structure of an aircraft includes an air-conditioning duct that is provided on each of a starboard side and a port side and guides conditioned air to a vicinity of a ceiling of a cabin in the aircraft. The air-conditioning duct includes a blowout portion and a blowout upstream portion. The blowout portion blows out the conditioned air to the cabin from an outboard side of the ceiling to an inboard side of the ceiling and toward a lower part than the ceiling, and the blowout upstream portion communicates with an upstream side of the blowout portion. In addition, the blowout portion or the blowout upstream portion is curved to cause a terminal end side of the blowout portion to be inclined downward with respect to a horizontal direction.

An environmental control system for an aircraft includes a first conduit, a second conduit, and a connector assembly. The connector assembly is coupled to the first conduit and the second conduit for controlling a flow of air. The connector assembly includes a connector, a connector ring, and an orifice plate. The connector includes at least one wall including a ridge defining a receptacle and a connector slot defined within the ridge. The connector ring is attached to the connector and defines a connector ring slot and a covering portion. The connector ring slot aligns with the connector slot and the orifice plate is inserted into through the connector ring slot and the connector slot into the receptacle during installation of the orifice plate. The covering portion covers the connector slot and retains the orifice plate within the receptacle during operation of the environmental control system.

An environmental control system for an aircraft includes a first conduit, a second conduit, and a connector assembly. The connector assembly is coupled to the first conduit and the second conduit for controlling a flow of air. The connector assembly includes a connector, a connector ring, and an orifice plate. The connector includes at least one wall including a ridge defining a receptacle and a connector slot defined within the ridge. The connector ring is attached to the connector and defines a connector ring slot and a covering portion. The connector ring slot aligns with the connector slot and the orifice plate is inserted into through the connector ring slot and the connector slot into the receptacle during installation of the orifice plate. The covering portion covers the connector slot and retains the orifice plate within the receptacle during operation of the environmental control system.

A partition for dividing a portion of an aircraft including at least a first inflatable cavity defined by a plurality of material sheets, and a nozzle configured to provide fluidic access to the first inflatable cavity, wherein the nozzle is configured to attach to an aircraft air vent.

A partition for dividing a portion of an aircraft including at least a first inflatable cavity defined by a plurality of material sheets, and a nozzle configured to provide fluidic access to the first inflatable cavity, wherein the nozzle is configured to attach to an aircraft air vent.

An overhead flow distribution assembly for an aircraft cabin, including a conduit defining a plenum having an inlet, upper outlets and lower outlets, the upper outlets spaced apart from each other along a longitudinal direction of the aircraft, the lower outlets spaced apart from each other along the longitudinal direction, the inlet being located between the upper outlets and the lower outlets, and a baffle extending within the plenum along the longitudinal direction, the baffle being located between the upper outlets and at least part of the inlet along a transverse direction normal to the longitudinal direction, the baffle having openings defined therethrough, the baffle configured to restrict airflow from the at least part of the inlet toward the upper outlets. A method of balancing a flow in an overhead flow distribution assembly for an aircraft cabin is also discussed.

An overhead flow distribution assembly for an aircraft cabin, including a conduit defining a plenum having an inlet, upper outlets and lower outlets, the upper outlets spaced apart from each other along a longitudinal direction of the aircraft, the lower outlets spaced apart from each other along the longitudinal direction, the inlet being located between the upper outlets and the lower outlets, and a baffle extending within the plenum along the longitudinal direction, the baffle being located between the upper outlets and at least part of the inlet along a transverse direction normal to the longitudinal direction, the baffle having openings defined therethrough, the baffle configured to restrict airflow from the at least part of the inlet toward the upper outlets. A method of balancing a flow in an overhead flow distribution assembly for an aircraft cabin is also discussed.

An aircraft pneumatic system including a pneumatic actuator arranged to operate at a pressure value at least equal to a pressure threshold, a line fluidly connected between a pneumatic source and the pneumatic actuator, and a venturi disposed upstream of the line and downstream of the pneumatic source. The venturi is configured to receive a source flow from the source at a mass flow rate, the mass flow rate being between a lower, nominal flow rate value and a higher, graded flow rate value. The venturi is sized such that when the mass flow rate is at the nominal flow rate value, a line pressure inside the line corresponds to a source pressure upstream of the venturi, and when the mass flow rate to the venturi is at the graded flow rate value, the line pressure is less than the source pressure.

An illuminated aircraft passenger cabin gasper comprises an air outlet for outputting a flow of air into an aircraft passenger cabin and an air guide, movably arranged within the air outlet for adjusting the flow of air that includes a light guide. The gasper also includes at least one light source, arranged adjacent to the light guide for coupling light into the light guide. The light guide has a light output surface for coupling light out of the light guide into the aircraft passenger cabin.

A temperature sensor for a first fluid senses a temperature of the first fluid downstream of a heat exchanger. A supply for a second fluid changes a temperature of the first fluid. The supply for the second fluid passes through the heat exchanger. A valve is positioned upstream of the said heat exchanger on the supply for the second fluid, and controls a flow rate of the second fluid diverted into a bypass line compared to a flow rate of the second fluid directed through the heat exchanger, with the three-way valve controlled by a control in response to feedback from said temperature sensor. The valve changes the respective flow rates delivered into the bypass line and through the said heat exchanger in a non-linear manner with a change in valve position. A manned spaceship is also disclosed.