Abstract: Double-curved aircraft door having a pair of stops in contact over a contact area. The isobarycentre (31A) of each contact area of a first lateral edge is substantially arranged in a first plane perpendicular to the longitudinal axis (21) and the same applies to a second lateral edge. For each contact area, the normal to the contact area passing through its isobarycentre (31A, 31B) substantially passes through the axis (41) of a medium cylinder (42). For each contact area, the normal to the contact area passing through its isobarycentre (31A, 31B) forms a deflection angle with a plane perpendicular to the longitudinal axis (21), the deflection angles of all the contact areas being equal.

Abstract: A mechanical drive connection assembly (1) for driving in rotation a carrier shaft (2) of a structure rotating about a central axis (2a) passing through this carrier shaft (2). This connection (1) includes at least one drive ring (3a) that is secured to this carrier shaft (2) and driven in rotation in a given direction (S1) by a transmission member (4a, 4b). This transmission member is connected at one end to the drive ring (3a) by winding and at its other end to a traction device. The rotation in the opposite direction (S2) is generated by a second traction device (5) connected to the carrier shaft (2).

Abstract: A device for emergency opening of an aircraft door having: a tubular actuating member (7) which includes a first end plate (8) and a second end plate (9); an elastic compression device having a tubular spring (10) compressed between the first end plate (8) and the second end plate (9); an expansion regulator (17, 18) arranged inside the tubular spring (10); a retaining member which includes at least one peripheral attachment connecting the first end plate (8) to the second end plate (9), the peripheral attachment being radially outside the tubular spring (10).

Abstract: A mechanism for locking an actuating handle of an aircraft door having laterally releasing stops and opens by circular translation, the door having a pivoting maneuvering arm coupled to a forearm articulated on the door and handle, in a plane parallel to the arm pivoting plane, between a closed position of the door and an end-of-travel position corresponding to partial opening thereof after releasing the stops, includes at least one peg borne by the handle and at least one guideway with a circular profile and borne by the arm face, the face arranged facing the peg and centered on the hinge, the peg and guideway being relatively positioned so, in the end-of-travel position of the handle corresponding to the end of the stops releasing and during the circular translation of the door until is fully open, the rotation of the handle is blocked by contacting the peg against the guideway.

Abstract: An assembly of a vehicle door (3) and of a panel (1) surrounding the door in which an edge protector (4) extends along a skin (3a) of the vehicle door facing the skin (1a) of the panel and has a portion disposed between the skins (1a, 3a) following when in a nominal position the geometric alignment of their exterior faces. This edge protector (4) has in a median portion (4b) a profile that is adapted to evolve and is made of an elastic material so that it has sufficient flexibility in a direction parallel to the distance between the skins (1a, 3a) and a transverse stiffness in the internal-external direction and its contact with the skin (1a) of the panel does not block opening of the door or damage the skins (1a, 3a).

Abstract: An aircraft door including a retaining device for a deployable evacuation device, the retaining device having at least: a beam; a first retention member fixed on a second end of the beam by a detachable clip, the first retention member being connected to the deployable evacuation device; a second retention member, which can be coupled to the first retention member, mounted on the door frame; retraction devices that moves between: an activated position, in which the second retention member is on the trajectory of the first retention member, and a deactivated position, in which the second retention member is outside the trajectory of the first retention member.

Abstract: An aircraft door including an external opening/closing lever (7) and an internal opening/closing lever (9) which are coupled by an engaging mechanism (12) which includes: a stop (24) which entrains a counter-stop (23) when the internal opening/closing lever (9) is in its closed position and the external opening/closing lever (7) is pivoted from its closed position to its open position; a lug (22) that rotates as one with the internal opening/closing lever; an engaging pawl (15) which is spaced apart from the path of the lug (22) in a passive position, and disposed on the path of the lug (22) in an active position; a support base (16) designed to push the engaging pawl (15) back into its passive position when the external opening/closing lever (7) is in its closed position.

Abstract: An emergency opening device (1) for an aircraft door having: a tubular operating member (2); elastic compression device (3). The operating member (2) includes a first end element (10) and a second end element (11) that can move in translation with respect to one another. The first end element (10) having a cylindrical retractable rotary stop (20), that can move between a first angular position of transmission and a second angular position of release.

Abstract: An emergency opening device (1) for an aircraft door having: a tubular operating member (2); elastic compression device (3). The operating member (2) has a first end element (10) and a second end element (11) that can move in translation with respect to one another. The first end element (10) includes a removable driving stop (20).

Abstract: The invention relates to an aircraft door having a support arm (6) connected to a support forearm (9) by a first pivot connection (7) about a first pivot axis (8), the support forearm (9) being connected to the leaf (5) by a second pivot connection (10) about a second pivot axis (11) parallel to the first pivot axis (8). The support arm (6) is connected to the door frame (4) by two hinges (13, 14) each having a pivot (26, 27) for rotating the support arm (6) about a third pivot axis (12) which is parallel to the first pivot axis (8) and to the second pivot axis (11), this pivot (26, 27) being connected to the door frame (4) by an attachment (22, 23) that is translatably adjustable in two directions (35, 37, 43, 47) orthogonal to one another and orthogonal to the third pivot axis (12).

Abstract: An aircraft door having: a first handling arm and a first forearm; a second handling arm and a second forearm; a holding device movable between: an immobilising position in which the first forearm and the second forearm are immobilised relative to the door panel; and a released position in which the first forearm and the second forearm are free to pivot relative to the door panel in at least one direction of rotation.

Abstract: The invention concerns an aircraft door having a lever (3) for emergency opening from outside, disposed in a lever window. The lever (3) for emergency opening from outside includes: a main arm (7) having a first aerodynamic surface (9); a profiled cowling (8) with a second aerodynamic surface (10); a driving stop (18) capable of rotating the profiled cowling (8) from its concealing position to its separated position when the main arm (7) passes from its retracted position to its deployed position.

Abstract: An installation for welding a stack of parts made of thermoplastic composite materials (20) in a local welding plane (P), this installation including an electromagnetic induction head (8), pairs of elements for guiding and pressing the workpiece stack (20) in this local plane (P), and, on each side of the induction head (8), at least one pair of guide elements, each pair of guide elements having a lower guide element (14) and an upper guide element (10) that are superposed, receiving between one another the stack of parts (20) by guiding it in the direction perpendicular to the local welding plane (P).

Abstract: An assembly for providing stabilising guidance to a semi-plug aircraft door equipped with an opening/closing mechanism. The door frame (3) is provided with stops (7) at the front and at the rear of the door with its stops (8) bears when it is closed. A door arm (4) links the door (2) to the door frame (3). A guiding connecting rod (6), referred to as a stabilising guiding connecting rod and located on a door edge (2h) extending parallel to the longitudinal axis of the vehicle, is mobile, being able to move in translation at one of its ends in relation to the door in the longitudinal direction of the aircraft during the phases of disengaging and re-engaging the stops (7, 8). During the swivelling and swivelling return phases, the stabilising rod (6) is locked to the door by a lever locking mechanism (9) being actuated by a return device.

Abstract: Aircraft door including a support arm (10) connecting a door leaf (5) and a door frame (13), the locking/unlocking mechanism of which includes: a control shaft (17) extending along a substantially vertical axis; a guide track (29); an actuating finger (32) attached to the support arm (10); the locking/unlocking mechanism having: an actuating configuration in which the actuating finger (32) is inserted into the guide track (29), the rotation of the control shaft (17) causing the actuating finger (32) to move along the guide track (29); a release configuration in which the actuating finger (32) is outside the guide track (29).

Abstract: An aircraft pressurized cabin door (1) having an outer panel (2) and a door structure (3) including: two circumferential beams (4) fastened to the lateral edges of the door; a plurality of longitudinal beams (5a, 5b) which are arranged substantially perpendicularly between the circumferential beams (4) and are fastened to the outer panel (2), each longitudinal beam (5a, 5b) extending from one circumferential beam (4) to the other. At least one longitudinal beam (5b) is a beam that has a variable cross-section which increases from the ends (B, M) of the beam to the center (H, L) of the beam, with two bent support bars.

Abstract: An aircraft door mounted in a fuselage in a reference frame X, Y, Z, having a casing, a door leaf and a support arm enabling the door leaf to be installed and the position thereof to be adjusted relative to the fuselage by a pair of fasteners. Each fastener (10, 40) includes a pivot (16, 46) rotatable about a common axis parallel to the axis Z, a base (13, 43) fastened to the casing (3), and a trolley (14, 44) movable on this base (13, 43), the base (13, 43) and the trolley (14, 44) of each fastener (10, 40) forming two translational adjustment links in directions parallel to the X and Y axes, these directions determining adjustment axes (11, 12; 41, 42) secant in a plane parallel to the plane XY.

Abstract: An aircraft door architecture having: a door (1); an ejector (3); an inflatable evacuation device (4); an emergency energy source (6) connected to the ejector (3) and to the inflatable evacuation device (4); a control unit (9) having the two following operating states: a nominal operating state in which the inflatable evacuation device (4) is kept in its retracted position and the emergency energy source is deactivated; an emergency operating state in which the emergency energy source (6) activates the actuation device of the ejector (3) in an emergency opening mode of the door (1), and activates the inflation device of the inflatable evacuation device (4) in an emergency inflation mode.

Abstract: An emergency opening device of an aircraft door including a tubular actuating member (2); a resilient compression device; a retaining member for retaining the tubular actuating member (2), having a retaining wire (12) which, when the tubular actuating member (2) is in the retracted position, is held taut between a first attachment (14, 17) and a second attachment (16, 18); a release device which includes a cutting member (22) for transversely cutting the retaining wire (12).

Abstract: This invention relates to an assembly of regions (10a, 10b) of composite parts (2a, 2b) with thermoplastic matrix, including a plurality of riveting points along regions (10a, 10) of the parts that overlap through the superposition of two faces (12a, 12b) of these regions (10a, 10b) which are positioned facing one another, each region (10a, 10b) having another, opposite, face (11a, 11b) which remains visible with the part (2a, 2b). The riveting is performed using assembly ties (6) made of thermoplastic resin-based composite material compatible with the material of the parts (2a, 2b). These ties (6), which are made up at least in part of a stitch of backstitch produced using a filament of a material selected from a fiber coated with aramid resin, a carbon fiber and a glass fiber, are embedded in said regions (10a, 10b) and passing right through the same with an orientation comprised between 30° and 90° with respect to their faces (11a, 11b; 12a, 12b).