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.

A rotorcraft having an aerodynamic device arranged below a rotor, which rotor participates at least in providing lift for the rotorcraft in the air, the rotor being mounted to rotate about a first axis of rotation, the aerodynamic device having a fairing provided with at least one air inlet for enabling a stream of cool air to flow from a region that is situated outside the rotorcraft to another region that is situated inside the rotorcraft; at least at a mouth of the at least one air inlet in the fairing, the aerodynamic device has at least one moving flap that is mounted to move in rotation, the at least one moving flap having at least one degree of freedom of movement in rotation about a second axis of rotation relative to the fairing, and the at least one moving flap orienting itself automatically and passively.

An in-flight safety enhancing system including: a combined automatic dependent surveillance broadcast (ADS-B) and carbon monoxide (CO) detecting device configured to receive an ADS-B transmission and obtain a CO reading; and a flight application executing on an aircraft crew computing device separate from the combined ADS-B and CO detecting device, and configured to: receive the ADS-B transmission and the CO reading; augment the flight application with information extracted from the ADS-B transmission; and provide a CO status notification when the CO reading exceeds a CO threshold value.

An air quality sensor includes a detector element array, a processor operatively connected to the detector element array, and a memory. The memory is disposed in communication with the processor and has instructions recorded on the memory that, when read by the processor, cause the processor to execute certain operations including measuring electrical resistance of one of more detector element of the detector element array. A difference is calculated between the measured resistance and a reference resistance, and a determination is made of presence or absence of a contaminant in air communicated to the detector element array from an atmosphere of an aircraft cabin based on the difference between the measured resistance and the reference resistance. Aircraft and methods of monitoring air quality also described.

The emergency oxygen supply for passengers in an aircraft comprises an oxygen source with a number of pulse breathing masks which are conductively connected to the oxygen source, wherein an individual shut-off valve which in the non-actuated condition is switched to block is provided in each conduit to a breathing mask. The emergency oxygen supply moreover comprises an impulse breathing control for actuating each individual shut-off valve, as well as an auxiliary conduit which connects the oxygen source to the breathing masks whilst bypassing the individual shut-off valves and which in each case via a check valve is connected to the respective conduit which leads to the breathing mask, or to the breathing mask itself. The auxiliary conduit is connected to the oxygen source via a central shut-off valve which is switched to open in the non-actuated condition.

The emergency oxygen supply for passengers in an aircraft comprises an oxygen source with a number of pulse breathing masks which are conductively connected to the oxygen source, wherein an individual shut-off valve which in the non-actuated condition is switched to block is provided in each conduit to a breathing mask. The emergency oxygen supply moreover comprises an impulse breathing control for actuating each individual shut-off valve, as well as an auxiliary conduit which connects the oxygen source to the breathing masks whilst bypassing the individual shut-off valves and which in each case via a check valve is connected to the respective conduit which leads to the breathing mask, or to the breathing mask itself. The auxiliary conduit is connected to the oxygen source via a central shut-off valve which is switched to open in the non-actuated condition.

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.

A passenger service unit, a passenger seating area, and a vehicle having a passenger service unit are provided, wherein the passenger service unit comprises a carrier element that can be extended in a longitudinal direction and a covering. The covering covers at least a section of the carrier element. At least one electrical and/or electronic element is integrated in the covering.