Abstract: An optical sensor configuration contains an optical current sensor and/or an optical voltage sensor. The sensor configuration further contains a first and a second hollow member, preferably ring shaped profiles, which are together disposed to form a hollow section. The sensor configuration further includes an optical fiber of the current sensor disposed in an annular groove, the groove being disposed at the boundary surface between the first hollow member and the second hollow member, and/or an optical fiber of the voltage sensor is disposed in a recess of the second hollow member. The first hollow member has an annular recess into which the second hollow member is disposed whereas the first hollow member is an L-shaped or U-shaped ring with two legs and the recess is formed between the two legs.

Abstract: This invention relates to a floor (4) for an aircraft, and preferably a cockpit floor, this floor comprising a plurality of spars (14) running along a longitudinal direction (X) of the aircraft and a plurality of cross-beams (16) assembled to the spars and running along a transverse direction (Y) of the aircraft, the floor also comprising attachment means (64) for assembly onto a sealed bottom (68) of the aircraft. According to the invention, the attachment means comprise a plurality of fasteners (66) each comprising at least one junction element with two opposite ends, each of the two opposite ends being articulated about an axis parallel to the (Y) direction.

Abstract: The invention relates to an aircraft floor (4), preferably a cockpit floor, this floor comprising a plurality of spars (14) running along a longitudinal direction (X) of the aircraft and a plurality of cross-beams (16) assembled to the spars and running along a transverse direction (Y) of the aircraft, the floor also comprising attachment means (64) used to assemble it to fuselage frames. According to the invention, the attachment means comprise a plurality of articulations (66) each connected to one end of one of the cross-beams (16), and enabling rotation about the (X) direction.

Abstract: The invention relates to an aircraft floor (4), preferably a cockpit floor, this floor comprising a plurality of spars (14) running along a longitudinal direction (X) of the aircraft and a plurality of cross-beams (16) assembled to the spars and running along a transverse direction (Y) of the aircraft, the floor also comprising attachment means (64) used to assemble it to fuselage frames. According to the invention, the attachment means comprise a plurality of articulations (66) each connected to one end of one of the cross-beams (16), and enabling rotation about the (X) direction.

Abstract: This invention relates to a floor (4) for an aircraft, and preferably a cockpit floor, this floor comprising a plurality of spars (14) running along a longitudinal direction (X) of the aircraft and a plurality of cross-beams (16) assembled to the spars and running along a transverse direction (Y) of the aircraft, the floor also comprising attachment means (64) for assembly onto a sealed bottom (68) of the aircraft. According to the invention, the attachment means comprise a plurality of fasteners (66) each comprising at least one junction element with two opposite ends, each of the two opposite ends being articulated about an axis parallel to the (Y) direction.

Abstract: A plug type door intended particularly for use on a military cargo type aircraft is designed to enable its ejection if necessary. To do this, an operating device such as a handle (28) simultaneously controls retraction of hinge pins (16c) from the hinges about which the panel (10) of the door is hinged to its frame (12) and retraction of the mechanical elements (21) against which the stops (19) fitted on the panel usually bear by gravity, when the door is closed. Furthermore, guide ramps connected to the frame (12) and in which the rollers supported by the panel (10) open downwards, to enable the panel (10) to drop by gravity when the handle (28) is pulled.