An access system for a vehicle includes a door moveably coupled to a portion of a fuselage. The door is configured to be moved between an open position in which an opening of an internal chamber is opened, and a closed position in which the opening of the internal chamber is closed. One or more actuators are secured to the door. The one or more actuators are configured to move the door between the open position and the closed position.

An aircraft door translation hinge assembly connects a passenger door of an aircraft to the aircraft fuselage structure and enables the passenger door to move through a desired opening motion. The opening motion of the passenger door is controlled by a simplified mechanism that utilizes a pair of linkages connected by a cam surface follower that engages in sliding engagement with a cam surface. The simplified mechanism controls a pivoting movement of the passenger door as the passenger door is first opened, and then controls a translation movement of the passenger door as the passenger door is continued to be opened from a passenger door opening in the aircraft fuselage.

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.

Aircraft door (1) including an opening (4), a frame (3), a hinge structure (5) and a circular translation guide device designed to maintain the orientation of the opening (4) during the opening or closing thereof. The hinge structure (5) is connected to the opening (4) by a lifting arm (8) allowing a lifting movement of the opening (4) relative to the hinge structure (5). The circular translation guide device includes a single link (11) connected to the frame (3) by one of the ends thereof and by the other of the ends thereof to a lever (13) which is attached to the hinge structure (5).

The present disclosure provides an aircraft door system including an aircraft door configured to translate from a closed position to an open position. The aircraft door system further includes a plurality of door pressure stops positioned along a length of the aircraft door and a handle coupled to the aircraft door. A rotation of the handle causes a first translation of the aircraft door in an inward direction and a forward direction. The aircraft door system further includes a hinge system coupled to the aircraft door. An outward force applied to the aircraft door causes a second translation of the aircraft door in an outward direction and a forward direction. The hinge system causes the aircraft door to translate such that the aircraft door remains parallel to the aircraft fuselage throughout an entirety of the second translation until the aircraft door reaches the open position.

Systems and methods for leak detection of aircraft doors. One embodiment is an apparatus for leak testing a seal between an aircraft door and a fuselage of an aircraft. The apparatus includes a structural frame that includes a suction cup configured to suction an outer surface of the aircraft door. The structural frame further includes legs to extend in length to push the structural frame away from the fuselage and cause the suction cup to pull the aircraft door toward an outside of the aircraft to tighten the seal between the aircraft door and the fuselage of the aircraft.

An actuating system for an actuatable door and to an actuatable door having such an actuating system. The actuating system comprises first and second rotatable latching shafts, a coupling link, first and second pivotable mechanical transmission elements that are mounted onto first and second rotatable latching shafts, respectively, and first and second latching members. First and second latching members are non-rotatably mounted to the second rotatable latching shaft and adapted for latching the actuatable door in a closed position. A first rotation of the first rotatable latching shaft results in pivoting of the first and second mechanical transmission elements and a second rotation of the second rotatable latching shaft, which causes a third rotation of first and second latching members.

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.

The invention relates to an opening system (10) for an auxiliary door (20) of an airplane in a fuselage (30), the door and the fuselage having skins in the extension of one another. In one exemplary embodiment, the system (10) includes a framing lintel (11) integrated into the fuselage, an upper beam (2S) of the door structure arranged opposite the lintel (11), and a set of three lever links (4A, 4B, 4C). Each link is connected, on the one hand, to the lintel (11) by a lever articulation (5a, 6a) fixed relative to the fuselage (30) and, on the other hand, to the upper beam (2S) by a lever articulation (5b, 6b) mobile with the door (20), the articulations (5a, 5b; 6a, 6b) being connected respectively to the lintel (11) and to the upper beam (2S) by fittings (41, 43; 42, 44). The set of links includes two types of link mounted alternately, in which the mobile articulation (5b, 6b) remains positioned respectively close to the fuselage skin (30) and further from this skin (30), the articulations (5a, 5b; 6a, 6b) of two adjacent levers (4A, 4B; 4B, 4C) forming an evolving quadrilateral.

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.