A door that is adapted to separating two environments with different pressures and to an aircraft with such a door. The door may include a door leaf, a door frame having a door stop and a roller, and an actuating system having a latch element and an inward-moving drive system. The inward-moving drive system may include a puller shaft and a puller that is non-rotatably attached to the puller shaft. The puller may include a guide rail that moves along the roller during a rotation of the puller such that the puller moves the door leaf in direction of the first environment thereby disengaging the latch element from the door stop.

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).

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.

An aircraft door lock having a bolt and a closure block, wherein the bolt is fastened in a movable manner to a door leaf structure and the closure block can at least partially receive the bolt. The closure block prevents any movement of the bolt in at least one direction, wherein the closure block is arranged on a portion of a hinge arm that overlaps the door leaf structure when the door leaf structure is in a closed position. Furthermore, an aircraft door having such an aircraft door lock, and an aircraft having such an aircraft door are described.

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).

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-place stresses directly across the fuselage opening via the door, as well as stops that react redial 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.

An aircraft door, and, more particularly, to an electromechanical door system for operating an aircraft door that closes an opening in the outer hull of an aircraft, as well as to a method of operating an electromechanical door system of an aircraft door that closes an opening in the outer hull of an aircraft. The electromechanical door system may be adapted for operating in a normal opening mode, an emergency opening mode, and a closing mode. If desired, the electromechanical door system may include a lifting and lowering lever, a lifting and lowering electric motor, and a gearbox that transmits a force from the lifting and lowering electric motor to the lifting and lowering lever.

An aircraft door arrangement, comprising a door pivotable between closed and open positions, a frame section in a door opening region, and an articulation arrangement connecting the door and frame section. First and second arms are mounted on the frame section, rotatable about first and second axes, respectively. Third and fourth arms are mounted on the door, rotatable about third and fourth axes, respectively. The second arm, at a first position, is rotatably coupled to the fourth arm about a fifth axis, and at a second position, closer to the second axis, is rotatably coupled to the third arm about a sixth axis. The third arm, at a third position, is rotatably coupled to the first arm about a seventh axis, and at a fourth position, closer to the third axis, is rotatably coupled to the second arm about the sixth axis. All axes are oriented substantially parallel.

An information projection and control system for projecting information onto a projection area provided by a vehicle door, comprising at least one control unit that generates information, for projection onto the projection area; at least one projection device that projects the generated information onto the projection area; and at least one movement sensor that detects movements in a sensing area associated with the projection area, wherein the at least one control unit is adapted to control generation of the generated information on the basis of the detected movements.

A system and method for an overwing exit door is provided. The overwing exit door system comprises a door, a handle connected to an inboard surface of the door, a guide track connected to a body of the aircraft, a roller, a first crank connected to the roller and associated with the handle, a first shaft system attached to the first crank, a latch system connected to the first shaft system, and a locking system associated with the latch system. The latch system comprises a rotating stop, a second crank associated with the rotating stop, and a second shaft system connected to the second crank and the rotating stop. These components together control operation of the overwing exit door between an open position and a closed position.