In some examples, a cabin pressure control and monitoring system includes an outflow valve, a first motor configured to operate the outflow valve to release fluid from a cabin, and a second motor configured to operate the outflow valve to release fluid from the cabin. The cabin pressure control and monitoring system also includes a first microcontroller configured to automatically control the first motor based on a pressure of the fluid in the cabin. The cabin pressure control and monitoring system further includes a second microcontroller configured to control the second motor based on user input and monitor the pressure of the fluid in the cabin. In some examples, a type of the first microcontroller is different than a type of the second microcontroller.

A variable chiller exhaust system incorporate a plurality of chillers, each chiller 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.

An outer surface of a part of an airframe includes a mixed region in which a first color similar to a color applied to an adjacent region and a second color having a lower absorption rate of sunlight than the first color are mixed in a predetermined color distribution pattern. A reflective material that contributes to an increase in a reflection rate of sunlight is added to a part to which at least the first color is applied in the mixed region.

An auxiliary power unit for an aircraft, having a compressor, an intercooler including first conduit(s) having an inlet in fluid communication with the compressor outlet and second conduit(s) configured for circulation of a coolant therethrough, an engine core having an inlet in fluid communication with an outlet of the first conduit(s), and a bleed conduit in fluid communication with the outlet of the first conduit(s) through a bleed air valve. The auxiliary power unit may include a generator in driving engagement with the shaft of the engine core to provide electrical power for the aircraft. A method of providing compressed air and electrical power to an aircraft is also discussed.

A Stability and Control Augmentation System (“SCAS”) module comprising one or more SCAS actuators, the or each SCAS actuator comprising a mechanical component that translates rotational motion to linear motion along a first axis of said SCAS; one or more electric motors for driving linear movement of the mechanical component in response to a command signal; and one or more angular transducers to detect the position of the SCAS actuator along the first axis.

A microtube heat exchanger is disclosed, including two end plates with an array of holes or openings and an array of microtubes disposed in the array of openings between the two end plates. The heat exchanger can be used in environmental control systems, including systems for aerospace applications.

An example temperature sensing device includes an air distribution inlet through which primary air is blown into via an environmental control system, a cabin air inlet through which secondary air enters from a passenger area of a fuselage and the cabin air inlet is coupled to the air distribution inlet through a duct and the secondary air is passively drawn into the cabin air inlet and to the duct due to a pressure difference present in the duct, and a temperature sensor coupled to the duct and positioned downstream of the cabin air inlet along an airflow path of the secondary air so as to be exposed to the secondary air drawn in through the cabin air inlet and flowing through the duct.

Heat exchanger assembly comprising a ram air flow channel (14) extending in a longitudinal direction, and characterized in that said assembly comprises: at least two separate heat exchangers (12a, 12b) that are adjacent in a transverse direction perpendicular to the longitudinal direction, are arranged in the ram air flow channel (14), and are configured such that the ram air passing through said channel (14) forms a cold pass of each heat exchanger (12a, 12b) by passing through said heat exchanger (12a, 12b) in said longitudinal direction, each heat exchanger (12a, 12b) also being configured for the passage therethrough of a fluid that is intended to be cooled and that forms a hot pass (20a, 20b); and an air passage which is provided between the heat exchangers and forms a thermally insulating air gap (18) between said exchangers (12a, 12b), and through which the ram air flows, said air passage extending in said longitudinal direction of said ram air flow channel (14).

The invention relates to an electrical air conditioning system for air conditioning a cabin (10) of an aircraft comprising a source (11) of fresh air, a dynamic air circulation duct (12), a motorized compressor (13) comprising an air inlet connected to said source of fresh air, and an air outlet connected to a primary cooling exchanger (PHx) housed in said dynamic air duct; an air cycle turbomachine (14) comprising at least a first compressor (15) and a first turbine (17) that are mechanically coupled to one another, said first compressor comprising an air inlet that can be connected either to said primary cooling exchanger (PHx) or to said source (11) of fresh air, and an air outlet connected to a main cooling exchanger (MHx) housed in said dynamic air duct, said first turbine (17) comprising an air inlet that can be connected either to a discharge port (54) for discharging stale air from said cabin or to said main cooling exchanger (MHx), and an air outlet that can be connected either to said cabin (10) or to an air injector (52) opening into said dynamic air duct.

A solar powered airship includes a cabin, at least one fuselage having an interior volume filled with a volume of a lighter-than-air gas such as helium, and a wing affixed to the fuselage. A plurality of solar panels are affixed to the wing and to the fuselage. A plurality of rotors are affixed to the wing, wherein each rotor is powered via an electric motor having a battery that is operably connected to the plurality of solar panels, thereby allowing for continuous flight. The solar powered airship may further include propellers, which may also be powered via the solar panels, or which may include gasoline powered motors. The solar powered airship can include various configurations and numbers of fuselages, wings, rotors, and propellers.