Computer-implemented methods for controlling the operation of aircraft, particularly electric or hybrid electric aircraft, are described. One such method, which may be implemented on a Flight Management System of the aircraft, comprises: receiving weather data indicative of weather conditions between a flight origin and a flight destination of the aircraft; and determining, using a constrained optimization method and a weather data dependent aircraft energy usage model, a three-dimensional flight path for the aircraft from the origin to the destination. The constrained optimization method may determine a flight path constrained by, amongst other things the energy required by an Environmental Control System of the aircraft.

Computer-implemented methods for controlling the operation of aircraft, particularly electric or hybrid electric aircraft, are described. One such method, implemented on a Flight Management System (FMS) of an aircraft, comprises: receiving, by the FMS, weather data indicative of weather conditions around the aircraft; and selecting, by the FMS, based on the received weather data, one of a plurality of different pre-defined FMS profiles, each FMS profile corresponding to a different range of weather conditions and defining a different set of aircraft operating parameters. The aircraft may be flown under the control of the FMS using the selected FMS profile.

Air conditioning system for an aircraft cabin, comprising a primary exchanger (14) configured to cool bleed air (12) from at least one compressor of the aircraft, a pre-compressor (18), an intermediate exchanger (20), a main compressor (22) configured to compress said pre-compressed bleed air, a main exchanger (28) configured to cool the compressed bleed air, and a water extraction loop, characterized in that it comprises a duct (108) for recovering at least part of the air from the cabin after it has passed through the cabin, and recovered air circulation ducts configured so that the recovered air successively passes through: a secondary exchanger (34), the recovered air forming a first cold source for cooling the bleed air again, a heat exchanger (20), the recovered air forming a second cold source for cooling the bleed air, an energy recovery turbine (48), the recovered air forming a source of energy.

An air gasper knob system for an overhead Passenger Service Unit (PSU) includes an annular gasper knob of a UV transparent material. The annular gasper knob defines an air passage therethrough, and extends about the air passage from a first annular end face to a second annular end face. The system also includes a UV illuminator mounted to the gasper knob, oriented to transmit UV illumination through the UV transparent material to sanitize exterior surfaces of the gasper knob. A method of sanitizing an air gasper knob comprises illuminating a gasper knob in an overhead PSU using UV illumination to destroy infectious agents on surfaces of the gasper knob.

An air distribution system for a cabin of an aircraft includes a supply air line with a supply air line connector, at least one air outlet with an air outlet connector, a riser line, which is connectable to the supply air line connector and the air outlet connector, and a trim element to be arranged on a primary structure of the aircraft inside the cabin. The riser line is flexible, wherein the trim element has an outer side which can be oriented relative to the primary structure and on which there is at least one retainer for retaining the riser line, and the at least one retainer is designed to be interlockingly connected to the riser line by being pressed against the latter, such that the riser line is fixed.

A system includes a primary heat exchanger with a first passage connected to a hot fluid source, a second passage connected to the first passage, and a third passage connected to the second passage and an outlet line. A compressor inlet is connected to the outlet line. A secondary heat exchanger is connected to a compressor outlet. First and second turbines are connected to an outlet of the secondary heat exchanger. A first load heat exchanger is connected to the first turbine. A second load heat exchanger is between the second turbine and a system outlet. A first valve connects the hot fluid source to the second and third passages. A second valve connects the first and second passages with the outlet line. A third valve is between the secondary heat exchanger and the second turbine. A fourth valve is between the first load heat exchanger and the system outlet.

A modular aircraft galley insert for performing thermal cycling for PCR testing includes a housing having a sample module for receiving a sample to be tested, a thermal module thermally connected to the sample module for cycling temperatures of the sample to be tested, a power module for providing power to the thermal module, a detector module configured to analyze the sample and connected to receive power from the power module, and a connectivity module for communicating results of a test from the detector module to a remote location with respect to the housing.

A method for collecting and testing particulates from aircraft air is disclosed. The method includes capturing particulates in at least one of an outlet flow path or a recirculation flow path with a collector over a period of time, removing the collector from at least one of the outlet flow path or the recirculation flow path for testing, concentrating the collected sample, conducting a test on at least one particulate captured in the collector, relaying a result of the test to a central data center to store the results, and identifying a previously non-described emerging pathogens within the results.

A system for monitoring aircraft air including a vessel having an inlet, a conical main body for extracting particles from the air coating an inner surface on the conical main body, and an outlet, wherein the outlet is to be positioned within at least one of an outlet flow path or a recirculation flow path of an aircraft, and at least one of an outflow valve positioned in the outlet flow path downstream from the collector or a HEPA filter positioned in the recirculation flow path downstream from the collector.

A system for monitoring aircraft air including a collector for collecting particulate samples positioned within at least one of an outlet flow path or a recirculation flow path of an environmental control system of an aircraft, wherein the collector is accessible to a user within the cabin of the aircraft.