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: 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: 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 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).

Abstract: Aircraft door (1) having an inside door opening lever (6) coupled to a vent flap (5) by a conditional opening mechanism having two modes and including a flap stop (20) to cooperate with a stop surface (21). The stop (20) has a first trajectory, the stop surface (21) being arranged outside this first trajectory of the flap stop (20). The stop (20) has a second trajectory, the stop surface (21) being arranged on this second trajectory of the flap stop (20).

Abstract: Device for opening an aircraft door in emergencies, said door being provided with an opening mechanism, including a device (2, 5) for actuating the opening mechanism, having: a tubular maneuvering member (2), and a second locking end (4) which has a stop surface (43); resilient compression device (5); a member for holding the second locking end (4), the holding member including a rotary lock (9) and a lever (44) which is suitable for cooperating with the stop surface (43), the rotary lock (9) being rotatable about the displacement axis of the maneuvering member (2); device (31) for activating the actuation device (2, 5) which are suitable for driving the rotary lock (9).

Abstract: An emergency opening device for an aircraft door provided with an opening mechanism includes an actuation device (2, 5) for actuating the opening mechanism, having: a tubular operating member (2) equipped with a second locking end (4) that includes a radial retaining finger (19); flexible compression device (5); a retaining member (9) for the second locking end (4), the retaining member (9) including a hook (28) which has a stop surface, the retaining member (9) being rotatable about the movement axis of the operating member (2); activation device (31) for the actuation device (2, 5), adapted to cause the retaining member (9) to open.

Abstract: An aircraft pressurized cabin door (1) having a fuselage panel (2) and a door structure (3) that includes: two circumferential beams (4) arranged on the lateral edges of the door (1); a plurality of longitudinal beams (5). Each longitudinal beam (5) is an open profile having an outer face to which the fuselage panel (2) is fixed and an inner face, the door structure (3) further including an internal force-absorbing frame (12) fixed to the inner face of each longitudinal beam (5), this internal force-absorbing frame (12) having a plurality of uprights (13) each extending opposite a circumferential beam (4), each upright (13) being fixed to several longitudinal beams (5).

Abstract: An emergency opening device for an aircraft door provided with an opening mechanism including an actuating device (2, 5) for the opening mechanism, which includes a tubular operating member (2); elastic compression device (5); an activation device (31) for the actuation device (2,5); the operating member (2) includes a first end element (10) and a second end element (11) which are freely translatable movable relative to each other along the movement axis (X).

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: 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: Aircraft door designed to assume a first configuration and a second configuration, having a bistable mechanism biasing the aircraft door towards either the first or second configuration, the bistable mechanism including: a first yoke having a base attached to the first member and a first pivot rotatably mounted on the bas; a second yoke having: a base attached to the first member; a lever a first end of which is mounted so as to pivot on the base; a second pivot mounted so as to rotate on the second end of the lever; a coupling device for coupling the lever to the second member of the door; an arch which can be elastically deformed by bending and a first end of which is attached to the first pivot and a second end attached to the second pivot.

Abstract: Method and device for manufacturing a profile member of composite material, the cross-section of which has three branches, including the steps of: —moving together two opposite edges of a panel (2) of sheet material in such a manner that these two opposite edges are juxtapositioned in one juxtapositioning direction; translating a pair of jaws (20) in a direction perpendicular to the juxta-positioning direction in such a manner that the pair of jaws (20) is positioned on either side of the opposite juxtapositioned edges, this translational movement of the pair of jaws (20) being carried out in the direction of a base (25); —simultaneously pressing the sheet material between the two jaws (20), on the one hand, and between the jaws (20) and the base (25), on the other hand; —finishing the profile member of composite material by hardening with a matrix with which the sheet material is impregnated.

Abstract: A method for manufacturing a beam (P1, P2) with closed section, the beam being produced by combining a first profile (P10, P20) and a second profile (P11, P21), including the following steps: producing the first profile by a first stamping of a first plate (5, 50) between a first punch (1, 10) having a first imprint and a second punch (2, 20) having a second imprint and incorporating a core (3, 30) modifying its second imprint; holding the first profile (P10, P20) on the first punch and positioning the core (3, 30) above the first profile (P10, P20); producing the second profile (P11, P21) by a second stamping of a second plate (6, 60) against the core (3, 30) between the first punch (2, 20) and the assembly formed by the superposition of the first punch (1, 10), the first profile (P10, P20) and the core.

Abstract: Aircraft door (1) having: an opening panel (2) provided with engagement abutments (26); a frame (3) intended to be attached to the fuselage (4) of the aircraft and including engagement counter-abutments (27); a hinge arm (5); a lifting lever (10); and a rotary control lever (20) which can be operated in a disengagement direction in order to unlock the opening panel (2). The door includes a one-way operating rod (18) which connects the control lever (20) to the lifting lever (10) and is designed to drive the lifting lever (10) only when the control lever (20) is actuated in the direction of disengagement.

Abstract: A door (3) of an aircraft (1) equipped with an opening/closing mechanism, the movement which is in a main horizontal plane (P) of the aircraft (1) is controlled by coupling between the door (3) and the frame (4) on a control ramp (7) and on two front (AV) and rear (AR) guides (8,9), arranged between the respective front (AV) and rear (AR), and the frame (4) coupled to at least one handling arm (5, 6) hinged in rotation on a front side (AV) of the frame (4) and to the door (3) via a forearm (5b, 6b).

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.