Abstract: A mixing device for an aircraft air conditioning system includes a plurality of cold-air supply lines, which are devised to supply cold air to the mixing device. A plurality of warm-air supply lines is further provided, which are devised to supply warm air to the mixing device. A first premixing chamber is connected to the cold-air supply lines and devised to mix the cold air that is fed through the cold-air supply lines into the first premixing chamber. A second premixing chamber is connected to the warm-air supply lines and devised to mix the warm air that is fed through the warm-air supply lines into the second premixing chamber. Finally, a main mixing chamber is connected to the first and the second premixing chambers and devised to mix the cold air premixed in the first premixing chamber with the warm air premixed in the second premixing chamber.

Abstract: A mixer for an aircraft air conditioning system has first and second fresh air lines and first and second recirculation air lines. A first premixer is connected to the first fresh air line and the first recirculation air line, to mix the fresh air with the recirculation air thereof. A second premixer is connected to the second fresh air line and the second recirculation air line, to mix the fresh air with the recirculation air thereof. A main mixer is connected by a first premixed air line to the first premixer and by a second premixed air line to the second premixer. The main mixer is adapted to be supplied through the first premixed air line and the second premixed air line exclusively with premixed air from the first and/or the second premixer.

Abstract: A supply system for supplying energy in an aircraft includes at least one electrical line including at least one core connectable to a pole of a current source, an electrically conductive shield, and a detection unit having at least two electrical inputs. The shield surrounds the at least one core under a distance and creates an intermediate space between the at least one core and the shield. At least one port of the detection unit is connected to the at least one core. At least another port of the detection unit is connected to at least one of the shield and the at least one core. The detection unit is adapted for detecting a differential current over the at least one core or an absolute current between the shield and a ground potential for generating a warning signal if a predetermined threshold value for the detected current value is exceeded.

Abstract: A supply system for supplying energy in an aircraft includes at least one electrical line including at least one core connectable to a pole of a current source, an electrically conductive shield, and a detection unit having at least two electrical inputs. The shield surrounds the at least one core under a distance and creates an intermediate space between the at least one core and the shield. At least one port of the detection unit is connected to the at least one core. At least another port of the detection unit is connected to at least one of the shield and the at least one core. The detection unit is adapted for detecting a differential current over the at least one core or an absolute current between the shield and a ground potential for generating a warning signal if a predetermined threshold value for the detected current value is exceeded.