An aircraft floor including at least one hinge connecting movable and fixed floor parts, which has a pivot axis parallel to a longitudinal direction. The floor also includes at least two beams, each including first and second beam portions secured respectively to the fixed and movable floor parts and connected together by a pivot link, and at least one rail including at least one first rail portion secured to the movable floor part and at least one second rail portion secured to the fixed floor part of the floor, extending the first rail portion.

Methods and apparatus to position a cargo unit in a cargo compartment of an aircraft are disclosed herein. An example linear track system in a cargo compartment of an aircraft includes a first linear synchronous motor (LSM) track coupled to a floor of the cargo compartment, a second LSM track coupled to the floor of the cargo compartment, and a cargo positioning system to activate the first and second LSM tracks to move a cargo unit along the first and second LSM tracks through the cargo compartment. A bottom of the cargo unit has first and second strips of conductive material to interact with the corresponding first and second LSM tracks.

An integral hybrid electric aircraft system including a fuselage including an electrical energy source, wherein the electrical energy source includes a plurality of batteries and a fuel tank, and wherein the fuel tank contains fuel. The fuselage also including a generator in fluid communication with the fuel tank. The generator generates electricity using the fuel from the fuel tank. The system including a set of propulsors, wherein each propulsor of the set of propulsors is electrically connected to the electrical energy source and the generator and wherein the set of propulsors is configured to be powered by the generator during fixed-wing flight. The set of propulsors including at least a pusher propulsor configured to provide forward thrust and at least a lift propulsor configured to provide lift.

An aircraft including at least one system rack positioned under a floor and including a series of vertical first uprights, distributed in a direction parallel to the longitudinal axis of the aircraft. The aircraft includes at least a first upper connecting system connecting at least one of the first uprights and a rail of the floor oriented parallel to the longitudinal axis. In so far as the first uprights of the system rack are not connected to the crossbeams of the floor, they can be positioned irrespective of the position of the crossbeams, and this contributes to simplifying the design of the system racks and allows these to be standardized.

An aircraft including at least one system rack positioned under a floor and including a series of vertical first uprights, distributed in a direction parallel to the longitudinal axis of the aircraft. The aircraft includes at least a first upper connecting system connecting at least one of the first uprights and a rail of the floor oriented parallel to the longitudinal axis. In so far as the first uprights of the system rack are not connected to the crossbeams of the floor, they can be positioned irrespective of the position of the crossbeams, and this contributes to simplifying the design of the system racks and allows these to be standardized.

An aircraft part has a fuselage portion and a floor, at least a part of which is joined to the fuselage portion via elastic link rods. Each elastic link rod is provided with a first end that is configured to be fixed to the floor and with a second end that is configured to be fixed to the fuselage portion. The elastic link rods are configured to exhibit a stiffness that makes it possible both to transmit loads between the floor and the fuselage portion and to absorb displacements brought about by deformations of the fuselage portion. The aircraft part thus making it possible, at a lower cost and with a lower mass, to obtain a connection between the floor and the fuselage portion that exhibits suitable elasticity to be able to transmit inertial loads while absorbing deformations of the fuselage portion.

A method for joining skin portions of a closed fuselage, in particular for an aircraft or spacecraft, has the following method steps: providing at least a first skin portion and a second skin portion, at least one of the skin portions being fitted with components to remain in the fuselage; positioning at least the first skin portion and the second skin portion relative to one another in a first joint such that the skin portions form a circumferentially closed fuselage arrangement; guiding a first joining head along the first joint on an outer surface of the fuselage arrangement; and guiding a second joining head along the first joint on an inner surface of the fuselage arrangement, the second joining head being guided along longitudinal guide means which are arranged inside the circumferentially closed fuselage arrangement and are formed at least in part by the components to remain in the fuselage.

A method for joining skin portions of a closed fuselage, in particular for an aircraft or spacecraft, has the following method steps: providing at least a first skin portion and a second skin portion, at least one of the skin portions being fitted with components to remain in the fuselage; positioning at least the first skin portion and the second skin portion relative to one another in a first joint such that the skin portions form a circumferentially closed fuselage arrangement; guiding a first joining head along the first joint on an outer surface of the fuselage arrangement; and guiding a second joining head along the first joint on an inner surface of the fuselage arrangement, the second joining head being guided along longitudinal guide means which are arranged inside the circumferentially closed fuselage arrangement and are formed at least in part by the components to remain in the fuselage.

An aircraft seating module (20) includes a seating mount (26) having a horizontal mounting rail (28) integrally joined to a vertical mounting post (30) at an adjoining elbow (32). The rail (28) includes a mounting boss (34) longitudinally spaced from the post (30) for attachment to an aircraft cabin seat track (18). Both the rail (28) and post (30) include mounting holes (38) for attaching a passenger seat (22) and appended furniture (24) directly to the seating mount (26) and in turn indirectly to the seat track (18) in the cabin floor (12).

An aircraft seating module (20) includes a seating mount (26) having a horizontal mounting rail (28) integrally joined to a vertical mounting post (30) at an adjoining elbow (32). The rail (28) includes a mounting boss (34) longitudinally spaced from the post (30) for attachment to an aircraft cabin seat track (18). Both the rail (28) and post (30) include mounting holes (38) for attaching a passenger seat (22) and appended furniture (24) directly to the seating mount (26) and in turn indirectly to the seat track (18) in the cabin floor (12).