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: A pressure measurement tool secured to a rod arranged across a duct of an engine of an aircraft. A sheath includes two walls which bound a space receiving the rod, the space communicating with the outside by an opening extending over the length of the sheath, the sheath having a bay extending over the length of the sheath and cavities distributed over the sheath. For each cavity, an air inlet including a passage opens at one end into the cavity another end into the duct. A printed circuit board runs along the bay. For each passage, a pressure sensor in the corresponding cavity faces the passage and is on the printed circuit board. A unit is provided for processing and/or recording the data transmitted by the pressure sensors. It is thus easy to install and makes it possible to take a large number of measurements in the secondary duct.

Abstract: A pressure measurement tool secured to a rod arranged across a duct of an engine of an aircraft. A sheath includes two walls which bound a space receiving the rod, the space communicating with the outside by an opening extending over the length of the sheath, the sheath having a bay extending over the length of the sheath and cavities distributed over the sheath. For each cavity, an air inlet including a passage opens at one end into the cavity another end into the duct. A printed circuit board runs along the bay. For each passage, a pressure sensor in the corresponding cavity faces the passage and is on the printed circuit board. A unit is provided for processing and/or recording the data transmitted by the pressure sensors. It is thus easy to install and makes it possible to take a large number of measurements in the secondary duct.

Abstract: The invention relates to a support device suitable for being installed in an arrangement referred to as “mounted” against the rear of a back of a seat comprising a headrest. The headrest is held at the top of the back by at least one upright. The support device includes a framework suitable for being positioned and supported on the top of the back, a clamp movable in relation to the framework, and at least one reversible fastener making it possible to fasten the clamp to the framework so as to immobilize the framework in relation to the upright.

Abstract: The invention relates to a support device suitable for being installed in an arrangement referred to as “mounted” against the rear of a back (90) of a seat (9) comprising a headrest (91), the said headrest (91) being held at the top of the said back (90) by at least one upright, the said support device comprising a framework (10, 31) suitable for being positioned supported on the top of the said back (90) a clamp (11) movable in relation to the said framework (10, 31) at least one reversible fastening means (12) making it possible to fasten the said clamp (11) to the said framework (10, 31) so as to immobilize the said framework (10, 31) in relation to the said upright.

Abstract: A flight test installation system for collecting aircraft data includes a sensor level configured to convert aircraft physical inputs into plural measurable electrical parameters, an acquisition level configured to perform at least one of an analogue, discrete or digital bus data acquisition to acquire each of the plural measurable electrical parameters, and a concentration level configured to receive data streams from each of the analogue, discrete and digital data buses, and to switch and duplicate frames in the received data streams without modifying a content of the data streams. The flight test installation system also includes a recording and analysis level configured to record and analyze the content of each of the data streams.

Abstract: The invention relates to a switched flight test installation with an architecture based on four data levels and for which all dated parameters are transported in a single <<packet>> type format: a first level (L1), or sensor level, in which the data are converted from a physical magnitude (pressure, temperature, force . . . ) into an electrical magnitude, a second level (L2), or acquisition level, in which the analogue, discrete or digital bus acquisition is made, a third level (L3), or concentration level, carrying data streams from all second level (L2) systems to fourth level (L4) systems, a fourth level (L4), or recording and analysis level.