A partition assembly (16) for an aircraft cabin, including a bulkhead (18) with first (28) and second (30) internal compartments having respective first (32) and second (34) open ends defined in a same side of the bulkhead (18), one of the compartments being located aft of the other, a sliding door (36) slidingly supported within the first compartment (28) and slidable out of the first compartment (28) through the first open end (32), and a curtain (42) slidingly engaged to a curtain rail (40), the curtain receivable in the second compartment (30) and slidable along the curtain rail (40) out of the second compartment (30) through the second open end (34). An aircraft curtain rail is also described where the curtain rail and curtain track each have a non-rectilinear profile when viewed in a first plane and when viewed in a second plane perpendicular to the first plane. A method of manufacturing a curtain rail is also discussed.

Systems and methods are provided by which a treatment fluid (e.g., a liquid corrosion inhibitor) may be applied onto the interior surfaces of an aircraft fuselage which employ an automated guided vehicle (AGV) comprising a carriage assembly and a robotic spray system carried by the carriage assembly supported by a support platform positioned laterally of an aircraft fuselage in alignment with the cabin door opening thereof. The AGV may thus be deployable through the cabin door opening of the fuselage to a deployed position within the interior of the fuselage so as to be moveable along a longitudinal axis of the fuselage to allow the robotic spray assembly to spray the treatment fluid onto interior surfaces of the fuselage. A sealing door assembly located rearwardly of the AGV which is moveable relative to a door opening in the fuselage may also be provided so as to sealingly close the door opening of the fuselage when the AGV is deployed within the interior of the fuselage.

A rotary wing aircraft with a fuselage that is equipped with at least one rail, comprising at least one sliding element, in particular a sliding door or a sliding window, that is slidably supported by the at least one rail, wherein the at least one sliding element is at least slidable along the at least one rail by means of an opening sliding movement into an opening movement direction from a fully closed position into a fully opened position, wherein a dampening unit is provided that dampens the opening sliding movement of the at least one sliding element upon reaching of the fully opened position.

An access device enables controlled or secure communication between different areas of an enclosure and, in the example illustrated in the present application of an aircraft, while providing reduced size. The access device includes at least three mobile walls able to move, independently from one another, to form a closed cylinder, the walls thus being in a so-called security vestibule position, and to overlap at least in twos in order to close off access to one or more areas while concealing the security vestibule, the walls thus being in a so-called retracted position. By overlapping at the access level of said areas that the walls allow to close, the device frees up the adjoining cabin space.

An adjustable sliding privacy screen for a premium class passenger suite may include a guide rail mounted to a wall partition. The adjustable sliding privacy screen may also include a yaw and roll adjustment bracket slidingly attached to the guide rail and to the screen. The yaw and roll adjustment bracket may include a flanged adjustment screw for adjusting the yaw and roll of the screen and a locking screw for securing the yaw and roll adjustment of the screen. The screen may also include a ball joint adjustment bracket slidingly attached to the guide rail and to the screen. The ball joint adjustment bracket may include a ball joint and adjustment screw for adjusting the pitch of the screen and a locking nut for securing the pitch adjustment of the screen. The device of the present invention thus allows for the adjustment of the yaw, roll, and pitch of the screen.

A vertical take-off and landing (VTOL) aircraft provides transportation to users of a network system. The network system may include multiple aircraft or other types of vehicles to provide multi-model transportation. An aircraft may include a fuselage, a truss coupled to the fuselage, and multiple distributed electric propellers coupled to the truss. The distributed electric propellers may be positioned on at least two different planes. The fuselage may include a cabin having one or more seats for the passengers arranged in a configuration that has a compact footprint, provides legroom, provides visibility to surroundings of the aircraft, or facilitates convenient ingress or egress of passengers. The aircraft may open a port cabin door and starboard cabin door for simultaneous ingress or egress of passengers.

A door management system on an aircraft includes a fuselage extending along a longitudinal axis in a fore-aft direction parallel to forward flight, an opening in a sidewall of the fuselage, a door mounted on the sidewall to slide in the fore-aft direction between a closed position covering the opening and an open position revealing the opening, a cable attached to the fuselage and the door and a speed governor operatively coupled to the cable to limit a velocity of the door as it moves between the open position and the closed position.

In order to simplify the connection of a door to the outer envelope of an aircraft cell, it is provided to dispose the door into a portion of the outer envelope having tilted sides, as is the case at the nose cones and the tail cones of conventional airplanes, and in various portions of blended wing body airplanes and flying wings. Thus, the door can be configured to displace, in rectilinear translation, from one of its extreme opening and closing positions to the other, without requiring that the door protrudes outside of the outer envelope in the closing position.

The system for controlling the speed of movement of a sliding door for an aircraft comprises a means for electromagnetically braking the door including a transmission shaft and electromagnetic resistive means. The resistive means are autonomous and include a control law relating a first damping value to a first speed threshold of the speed of movement of the door, a second damping value to a second speed threshold of the speed of movement of the door, the resistive means applying on the transmission shaft the resistive torque equal to a first torque proportional to the first damping value when the speed of movement is higher than the first speed threshold, and applying the resistive torque equal to the sum of the first torque and of a second torque proportional to the second damping value when the speed of movement is higher than the second speed threshold.

An aircraft having a sponson extending substantially transversely relative to a main body of the fuselage of the aircraft and substantially perpendicularly relative to a vertical anteroposterior plane of symmetry P of the main body of the fuselage when the aircraft is standing on a horizontal support, the sponson including a notch locally reducing a cross-section of the sponson in a connection zone of the sponson, the connection zone being suitable for being arranged in the immediate proximity of the main body of the fuselage of the aircraft from which the sponson emerges transversely, the notch being open at least to a front outside face and to a top outside face of the sponson and being suitable for receiving a bottom portion of a sliding side door when in its open position.