A method of diagnosing a fault in a cabin temperature control system of an air-conditioning system of an aircraft includes transmitting multiple temperature sensor readings from temperature sensors operably coupled to the air-conditioning system, comparing the transmitted multiple temperature sensor readings to related reference values, and diagnosing a fault in the cabin temperature control system based on the comparing.

An air distribution panel for aircraft comprises a primary air inlet port, a housing fluidly coupled to the primary air inlet port, and an environmental sensor. The primary air inlet port is configured to be fluidly coupled to and receive primary air from an air distribution plenum. The housing comprises an air outlet chamber and a secondary air inlet chamber. The primary air is exhausted into an aircraft compartment via the air outlet chamber. Secondary air is drawn from the aircraft compartment via the secondary air inlet chamber. Exhausting of the primary air through the air outlet chamber causes the secondary air to be passively drawn into the secondary air inlet chamber. The environmental sensor is positioned within the secondary air inlet chamber and along an airflow path of the secondary air. The secondary air is exhausted via the air outlet chamber back into the aircraft compartment after the secondary air passes the temperature sensor.

An air distribution system and method and an associated climate control device are provided for an aircraft in order to allow for more granular control of the temperature of the conditioned air distributed through the cabin of the aircraft. In one example, an air distribution system and method are configured to provide for individual temperature control within different zones of an aircraft, such as by associating a thermocouple device with a respective air distribution subsystem that delivers conditioned air to a respective zone. In another example, a climate control device is configured to allow individualized temperature control of the air discharged through a vent by associating a thermocouple device with the respective vent, thereby allowing for individual temperature control for a passenger onboard the aircraft.

An air conditioning system for a seat, comprising an arm rest (4a, 4b) of the seat, the arm rest having a top side, an inner wall, an outer wall, a front end, and a back end defining a hollow interior between them, means for providing air conditioned to a desired temperature, from an air source to the hollow interior of the arm rest, and a plurality of nozzles formed through the inner wall, defined between a nozzle inlet on an inner surface of the inner wall facing into the hollow interior and a nozzle outlet on an outer surface of the inner wall facing towards a seating area of a person when sitting in the seat, the nozzles providing a path through which air flows from the hollow interior, into the nozzle inlet and out of the nozzle outlet.

An aircraft structure which extends along a longitudinal axis, a lateral axis and a vertical axis, wherein the aircraft structure includes an upper shell and a lower shell that together surround an interior compartment designed for accommodating an aircraft cabin, and a pillar arrangement with at least one support pillar which extends through the interior compartment and connects the upper shell to the lower shell and supports same in relation to each other. An aircraft structure can be provided which is particularly efficient, in particular has a low weight and requires little space and outlay on assembly is achieved in that the interior of the support pillar has at least one flow duct for the conduction of air-conditioned air.

A variable chiller exhaust system incorporate a plurality of chillers, each driller having an inlet receiving air from a crown in an aircraft fuselage and an outlet connected to a manifold. A plurality of check valves are connected to the manifold and configured to maintain a differential back pressure on the plurality of chillers of 2 water pressure or less. The check valves vent into the crown. An exhaust conduit is connected to direct air from the manifold to a variable speed fan. An outflow valve exhausts air from the variable speed fan to an exterior of the fuselage.

A suite management system is provided. The suite management system includes a controller. The controller is configured to obtain passenger preferences from a passenger occupying a suite, obtain circadian data from the passenger, analyze the circadian data to identify one or more changes to the suite to align with the passenger preferences, and, responsive to identifying the one or more changes, automatically adjusting one or more electronic devices within the suite to align with the passenger preferences.

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.

A processing system deployed in a carrier transport vehicle may establish a wireless communication session with a mobile device of a user, assign a zone of the carrier transport vehicle to the user, the zone including a plurality of network-connected devices, obtain a user profile from the mobile device of the user, determine at least one biometric sensor accessible via the mobile device of the user, obtain biometric data of the user from the at least one biometric sensor accessible via the mobile device of the user, determine a condition of the user based upon the biometric data, identify at least one adjustment to at least one of the plurality of network-connected devices in response to the condition of the user that is determined and the user profile, and apply the at least one adjustment to the at least one of the plurality of network-connected devices.