A system for opening a door of an aircraft includes a connection assembly adapted to connect the door to a fuselage section of the aircraft. The connection assembly includes a main hinge pivotally connected to the fuselage section and a link assembly connecting the door to the main hinge and pivotally connected to the fuselage section, the link assembly including one member slidingly and pivotally connected to the door. The system also includes a latch mechanism between the door and the main hinge, the latch mechanism being adapted to be actuated. The system is adapted to move the door upwardly and inwardly along a predetermined path without moving the main hinge through movement of the latch mechanism and, subsequently, to pivot the door around a virtual pivot point located outside of the aircraft by moving the main hinge once the door has reached an end of the predetermined path.

A flying wing or blended body aircraft comprising at least one door installed in the leading edge of the aircraft. The lateral edges of the door extend each in a plane parallel to the plane of symmetry of the aircraft, when the door is closed. It reduces the aerodynamic penalties of a door installed in the leading edge of such an aircraft. It also reduces noise related to airflow at the door, and improves the robustness of the aircraft with respect to impacts.

It describes an aircraft access door, in particular a boarding and landing access door arranged centrally on a fuselage portion of the aircraft and perpendicularly relative to a longitudinal axis of the aircraft, the access door being formed by a wing fairing disposed adjacent to a fuselage floor and a fuselage fairing associated with the wing fairing, the wing fairing being provided with rotational means positioned below the floor, the fuselage fairing being provided of access means interconnecting the floor to the ground.

It further describes an aircraft provided with an access door, particularly a boarding and landing access door, arranged centrally on a fuselage portion of the aircraft and perpendicularly to a longitudinal axis of the aircraft.

Systems and methods for securing an emergency exit door on an armrest of a seat are provided. A system includes a latch connected to an armrest of a seat of a vehicle. The latch is moveable relative to the armrest between a stowed position and a deployed position. The latch is structured and arranged to engage an edge of a door that is associated with an exit of the vehicle to hold the door on the armrest.

Systems and methods for securing an emergency exit door on an armrest of a seat are provided. A system includes a latch connected to an armrest of a seat of a vehicle. The latch is moveable relative to the armrest between a stowed position and a deployed position. The latch is structured and arranged to engage an edge of a door that is associated with an exit of the vehicle to hold the door on the armrest.

A vehicle door unit comprises a rotating lever supported rotatably about a first shaft at a first end, a door mounting coupled rotatably about a second shaft to a second end of the rotating lever, a door attached to the door mounting and being configured to cover an opening in a vehicle and to close off a vehicle interior, and a drive unit configured to rotate the rotating lever about the first shaft between a closed position and an open position. The rotating lever is configured to move the second shaft, on a movement from the closed position to the open position, on a circular path, due to which the door mounting is first moved into the vehicle interior and, on further rotation of the rotating lever, out of the vehicle interior.

A door assembly, particularly for doors of passenger aircraft, includes a door frame, a door having a door body hingedly installed in the door frame, at least one hooking pintle attached to the door frame or an edge of the door body extending along a pintle axis, and at least one door latch connected to an edge of the door body or the door frame, respectively, the door latch having a substantially C-shaped latch body configured to rotate around an axis parallel to the pintle axis of the hooking pintle. The door assembly further includes a bistable latch and hook mechanism configured to catch the door latch in hooking engagement with the hooking pintle and to retain the door latch in a direction perpendicular to the door body in an overcenter position.

A device for opening an aircraft door, comprising: a support arm arranged between the aircraft fuselage and the aircraft door; an opening system for opening the aircraft door; a support arm cover covering the support arm in the closed position of the aircraft door, the support arm cover having a cover element, and a flap element which swivels between being flush with the cover element, and a state in which the flap element overlaps the cover element; and a guide system for guiding the flap element, wherein the guide system has at least one guide arm, one end of which is joined in an articulated manner to the support arm, and the other end of which is joined to at least one guide element, which guide element can be guided along a guide track on the inner side of the flap element, when the aircraft door is opened.

Systems and methods for securing an emergency exit door on an armrest of a seat are provided. A system includes a latch connected to an armrest of a seat of a vehicle. The latch is moveable relative to the armrest between a stowed position and a deployed position. The latch is structured and arranged to engage an edge of a door that is associated with an exit of the vehicle to hold the door on the armrest.

An aircraft door mechanism includes at least an aircraft structure that delimits an opening, and an aircraft door mounted so as to be movable relative to the structure between a closed position that closes the opening, and a boarding position, in which the door is arranged away from the opening and in which passengers are able to board the aircraft structure through the opening. The aircraft door mechanism includes also a control system configured so as to control the execution of a closing operation and the execution of an opening operation of the door, the control system including a drive shaft, with the control system being configured so as to control the execution of said operations by means of continuous rotation of the drive shaft relative to the aircraft structure.