An aircraft door mechanism includes an aircraft structure (14) delimiting an opening (24); an aircraft door (26) movable between a position closing off the opening (24) and a released position of the opening (24); and a guide system (28) for moving the door (26) between the closed off and released positions. The guide system (28) includes a main rail (46) that is fixed relative to the structure and a main carriage (48) mechanically connected to the door (26) and able to slide on the main rail (46) during the movement between said closed off and released positions. The main rail (46) is positioned between the door (26) and the structure during at least part of the movement of the door (26) between said closed off and released positions.

An aircraft of flying wing or blended wing body type comprising, for access to a pressurized housing, a non-pressurized door in the trailing edge of the aircraft and a pressurized door on the pressurized housing. The distance between the center of the pressurized door and a plane of symmetry of the aircraft is less than or equal to the distance between the center of the non-pressurized door and the plane of symmetry, and the pressurized door is outside a rear wall of the pressurized housing or upstream of a rear extremum point of the housing in the absence of any such rear wall. This aircraft has optimum aerodynamic performance and the circulation of passengers between the pressurized housing and the exterior of the aircraft may be fluid.

A short term, autonomous, electrical power supply system, particularly an emergency short term, autonomous, electrical power supply system. Said system comprises an actuator with an electrical motor (14), an electrical generator (15) for driving said electrical motor (14) of said actuator, a turbine (13) in driving engagement with said electrical generator (15), an generator (7) of combustible, fluidic energy, a fluid line (10) from said generator (7) to said turbine (13), a control unit (5), and an igniter (9) arranged inside said generator (7) and controlled by said control unit (5).

A connecting mechanism between an aircraft door and a structure of the aircraft, a related aircraft and method are provided. The connecting mechanism includes an arm intended to be hinged on to the structure, a rotating connection between the door and the arm. The rotating connection may be disengaged from a connection configuration for connecting the door with the arm in an open position of the door, into an uncoupling configuration for uncoupling of the door from the arm, in a closed door position of the door.

A door system for an aircraft includes a door frame defining a door opening with a first perimeter strut and a second perimeter strut spaced apart from the first perimeter strut, at least one first frame stopper attached to the first perimeter strut and at least one second frame stopper attached to the second perimeter strut. The frame stoppers each comprise a first contact portion projecting into the door opening and having a first toothing. The first toothings are each formed on an inner surface of the first abutment portion. Further, the door system comprises a door mounted movably relative to the door frame and disposed in the door opening in a closed state, and a number of door stoppers corresponding to the number of frame stoppers disposed on opposite sides of the door and connected to the door, each door stopper having a second abutment portion. The second abutment portion comprises a second toothing formed complementary to the first toothing. The first toothing of a respective frame stopper and the second toothing of a respective door stopper engage in each other in the closed state of the door.

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).

The invention proposes a simple system, with small space requirement, without hinge arms or sealing skirt, while providing secure and effective opening. To achieve this, the invention provides a door opening by a lateral guidance defining an integrated doubling-back kinematics, towards the interior then the exterior of the fuselage. An opening system of an emergency door (1) is positioned in an aircraft fuselage (2), the door and the fuselage comprising respective frameworks (11, 21) extending opposite each other. According to the invention, the system comprises a control handle (5) for rotating, combined with a bolt/latch pair, and an opening mechanism (30) equipped, in the upper corner areas (Zs) of the door (1), with a pivoting lever (6) hinged on an upper edge of the fuselage (2) and provided with guide tracks interacting with the bulk/latch pair and with a door attachment fitting (12), upper and lower rollers mounted in the lateral framework of the door (11c) in connection with the guide tracks (20s, 20i) mounted in the opposing fuselage framework (21c), the upper guide tracks (20s) being inclined rising towards the interior of the cabin (I) and the lower guide tracks (20i) being curved.

Apparatus, systems, and methods for selectively locking and unlocking a passenger door. The apparatus includes a first shaft, having a first longitudinal centerline, and a member, connected to the first shaft. A handle is connected to the first shaft via the member, the handle being movable via rotation of the first shaft from a locked position and an unlocked position. A first protrusion extends from the handle and a latch crank is connected to the second shaft. A second protrusion extends from the latch crank and a linkage is connected between the latch crank and the member. When the handle in the locked position, the first protrusion is positioned adjacent to the second protrusion to prevent rotation of the second shaft. When the handle is in the unlocked position, the first protrusion is positioned away from the second protrusion to enable the second shaft to rotate.

A plug door assembly for a pressurized aircraft is provided. The door assembly includes a surround and a door, and connector assemblies along the edges that act to transfer in-plane stresses directly across the fuselage opening via the door, as well as stops that react radial loads generated by cabin pressure. The door assembly obviates the need for a separate frame to transmit stresses around the perimeter of the fuselage opening.

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.