Abstract: A display system comprising a bell with a lateral wall and a ceiling, delimiting between them an internal volume with an opening opposite the ceiling, a depressurizing arrangement configured to produce a depressurization in the internal volume, an image capturing device at the ceiling, a display screen, and a processing unit receiving an image from the image capturing device and sending the image to the display screen.

Abstract: A display system comprising a bell with a lateral wall and a ceiling, delimiting between them an internal volume with an opening opposite the ceiling, a depressurizing arrangement configured to produce a depressurization in the internal volume, an image capturing device at the ceiling, a display screen, and a processing unit receiving an image from the image capturing device and sending the image to the display screen.

Abstract: The invention relates to an aircraft (10) having a system for measuring a static reference pressure in flight, which system comprises: a pressure sensor (22) connected to the rear portion of the aircraft by a cable (16) and associated with a pressure intake (24) that is located, in flight, in an undisturbed zone downstream from the aircraft, the pressure signal (22) being suitable firstly for measuring a pressure coming from the pressure intake (24) and secondly for transmitting a signal representative of the measured pressure, e.g. an electric signal, to the aircraft; and a system (34) on board the aircraft, which system is suitable for determining a pressure measurement firstly from the transmitted signal and secondly from a position of the pressure sensor (22) relative to the aircraft (10). Pressure is measured dynamically while the aircraft is climbing or descending.

Abstract: A device for testing pneumatic circuits and for measuring the leakage rate from reference pressure lines onboard an aircraft, connected to a plenum chamber. The device includes a multi-pressure system, comprising several sensors each connected to a reference pressure line, first solenoid valves arranged on the input channels to this multi-pressure system, and connected to the reference pressure lines through first connectors, second solenoid valves arranged on the reference pressure lines, a pressure controller module that is connected to all the first solenoid valves through a second connector, an electronic board that controls the solenoid valves and calibration of the multi-pressure system, a control device. The invention also relates to a method making use of this device.

Abstract: The invention relates to an aircraft (10) having a system for measuring a static reference pressure in flight, which system comprises: a pressure sensor (22) connected to the rear portion of the aircraft by a cable (16) and associated with a pressure intake (24) that is located, in flight, in an undisturbed zone downstream from the aircraft, the pressure signal (22) being suitable firstly for measuring a pressure coming from the pressure intake (24) and secondly for transmitting a signal representative of the measured pressure, e.g. an electric signal, to the aircraft; and a system (34) on board the aircraft, which system is suitable for determining a pressure measurement firstly from the transmitted signal and secondly from a position of the pressure sensor (22) relative to the aircraft (10). Pressure is measured dynamically while the aircraft is climbing or descending.

Abstract: A device for testing pneumatic circuits and for measuring the leakage rate from reference pressure lines onboard an aircraft, connected to a plenum chamber. The device includes a multi-pressure system, comprising several sensors each connected to a reference pressure line, first solenoid valves arranged on the input channels to this multi-pressure system, and connected to the reference pressure lines through first connectors, second solenoid valves arranged on the reference pressure lines, a pressure controller module that is connected to all the first solenoid valves through a second connector, an electronic board that controls the solenoid valves and calibration of the multi-pressure system, a control device. The invention also relates to a method making use of this device.

Abstract: A device for measuring the flow speed of a fluid as well as its direction and its orientation, based on a thermal-sensor measurement principle, that comprises at least three flow measurement probes each having a sensitive member and an obstacle masking a predetermined measurement area of the sensor, characterized in that the flow measurement probes are attached on carrier posts, the carrier posts defining the obstacles that form masking members for an angular sector of the flow measurement probes facing the sensitive member of the probes.

Abstract: A device for measuring the flow speed of a fluid as well as its direction and its orientation, based on a thermal-sensor measurement principle, that comprises at least three flow measurement probes each having a sensitive member and an obstacle masking a predetermined measurement area of the sensor, characterized in that the flow measurement probes are attached on carrier posts, the carrier posts defining the obstacles that form masking members for an angular sector of the flow measurement probes facing the sensitive member of the probes.