Aircraft window assemblies and methods. The aircraft window assemblies comprise a window frame configured to support a window pane on an aircraft skin about a window aperture defined in an aircraft skin. The window frame includes a base formed of a continuous fiber reinforced thermoplastic composite and at least one overmolded feature molded to the base. The base defines a central aperture and includes circumferential flange portion configured to support the base on the aircraft skin surrounding the window aperture and a skirt portion extending inwardly from the circumferential flange portion and surrounding the central aperture. The skirt portion is non-planar with the circumferential flange portion and comprises a support surface for the window pane. The methods comprise forming the window frame, which comprises stamp-forming the base of the window frame from a continuous fiber reinforced thermoplastic composite sheet and overmolding the at least one overmolded feature to the base.

A laminated glazing includes a first and a second glass sheet that are bonded by a first interlayer adhesive layer, a peripheral zone of the laminated glazing being covered by a stepped metal element, the laminated glazing including a heating network of wires and/or a heating electrically conductive layer that is provided with busbars, a plurality of probes and other optional electrical elements that are linked to an electrical power supply via the connector of the laminated glazing, an electrical conductor linking the stepped metal element to a busbar of the heating network of wires and/or of the heating electrically conductive layer; and/or to the cap of the connector of the laminated glazing, which is linked to the ground of the structure for mounting the laminated glazing; and/or to a contact of the connector.

A method for producing a frame component for a door frame structure of an aircraft. A connecting zone is generated on a first and a second assembly surface of a connecting component in each case by generating a surface texture on the assembly surfaces, wherein the connecting component is formed from a metal material. The assembly surfaces of the connecting component are placed against a door frame member and against an attachment member, wherein the door frame member and the attachment member are each formed from a fiber-reinforced thermoplastics material. Furthermore, the connecting component and the door frame member are welded, and the connecting component and the attachment member are welded. A frame component and a door frame structure are also described.

In order to simplify the kinematics involved in opening an aircraft door, a plurality of mobile stop members is provided at the periphery of the door, these being intended to press against complementary stop arrangement provided on the door frame. A door control device is configured to bring the door from its closed position into a set-back intermediate position by moving it towards the interior of the compartment, and a stop arrangement control device is configured to allow the mobile stop members to be moved, when the door is occupying its set-back intermediate position, from a deployed locking position to a retracted unlocking position, allowing the door to be moved outward through the opening in the fuselage.

Vertical take-off and landing (VTOL) aircraft can provide opportunities to incorporate aerial transportation into transportation networks for cities and metropolitan areas. However, VTOL aircraft can be sensitive to uneven weight distributions, e.g., the payload of an aircraft is primarily loaded in the front, back, left, or right. When the aircraft is loaded unevenly, the center of mass of the aircraft may shift substantially enough to negatively impact performance of the aircraft. Thus, in turn, there is an opportunity that the VTOL may be loaded unevenly if seating and/or luggage placement is not coordinated. Among other advantages, dynamically assigning the VTOL aircraft payloads can increase VTOL safety by ensuring the VTOL aircraft is loaded evenly and meets all weight requirements; can increase transportation efficiency by increasing rider throughput; and can increase the availability of the VTOL services to all potential riders.

An aircraft door, an aircraft region and an aircraft with an aircraft door. The aircraft door through which passengers enter and leave the aircraft and is held towards the outer side by stops and is locked exclusively on a hinge side opposite the stops. Also, an aircraft region and an aircraft with such an aircraft door.

A vertical takeoff and landing (VTOL) aircraft, including: a vehicle controller circuit programmed to operate the VTOL aircraft without an onboard human operator; a rotor system; an airframe; and an external cargo coupling to receive an external payload of at least approximately 300 pounds beneath the airframe.

A bench seat assembly that includes a first seat that includes a seat portion and a back, a second seat that includes a seat portion and a back, and a center portion positioned between the first and second seats. The first seat is bifurcated by a first vertical plane, the second seat is bifurcated by a second vertical plane, and the center portion is bifurcated by a center vertical plane. The first seat is angled outwardly such that the first plane defines a first acute angle with the center plane and the second seat is angled outwardly such that the second plane defines a second acute angle with the center plane. The first acute angle and the second acute angle are approximately the same.

A removable barrier and an aircraft including such a removable barrier. The barrier including a panel configured to block at least partly an opening delimited by a frame, a plurality of straps each connected to the panel and each having first and second ends, for each strap, a first connection configured to connect the first end of the strap and a first edge of the frame at least temporarily, a second connection configured to connect the second end of the strap and a second edge of the frame at least temporarily, at least one folded overlength at the level of at least one of the first and second ends of the strap, at least one breakable connection keeping the overlength folded.

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.