An embodiment of the present disclosure provides a method and apparatus for supplying an electrical current. The method comprises sending the electrical current into a device from a panel comprising a dielectric core. Further, the method comprises a first sheet with a first conductive adhesive attaching the first sheet to a first side of the dielectric core, wherein the first conductive adhesive is a first electrode for a battery. Yet further, the method comprises a second sheet with a second conductive adhesive attaching the second sheet to a second side of the dielectric core, wherein the second conductive adhesive is a second electrode for the battery. Still further, the method comprises operating the device using the electrical current from the battery in the panel.

A method for manufacturing a lining panel with integrated electric lines for a lining of a passenger cabin of an aircraft or spacecraft includes using an additive manufacturing (AM) or 3D printing technique to form the electric lines on or into a panel body of the lining panel. A lining panel with integrated electric lines for a lining of a passenger cabin of an aircraft or spacecraft includes a panel body and electric lines being formed on or into the panel body using an AM or 3D printing technique.

There is provided a raceway cover assembly for installing conductive element(s) in an aircraft. The raceway cover assembly includes a raceway cover for removable coupling to a raceway. The raceway is configured for attachment to a sidewall assembly for use in a cabin of the aircraft. The raceway cover includes a first cover side, a second cover side, and retaining element(s) disposed on the first cover side. The raceway cover assembly further includes the conductive element(s) coupled and retained to the first cover side, with the retaining element(s), to form the raceway cover assembly. The conductive element(s) and the raceway cover are assembled together at a location off of the aircraft, prior to installing the raceway cover assembly with the one or more conductive elements in the aircraft, which allows for routing of the one or more conductive elements in the raceway cover at the location off of the aircraft.

A connection assembly for connecting a first element to a second element is provided. The connection assembly has a male element and a female element. The female element has a barrel nut. The barrel nut has a conical inner portion positioned at a first longitudinal region and a cylindrical inner portion positioned at a second longitudinal region. The barrel nut has a first engaging element portion and a first plain portion arranged alternatingly around a circumferential direction of the barrel nut. The male element has a cylindrical bolt-like shape and has a second engaging element portion and a second plain portion arranged alternatingly around a circumferential direction of the male element. The male element further has flattened sides at the second plain portion. The second engaging element portion of the male element is configured to engage with a respective one of the first engaging element portion of the barrel nut.

An aircraft assembly may comprise an interior aircraft monument, an aircraft structure, and a load absorbing tie rod coupled to the interior aircraft monument and the aircraft structure. The load absorbing tie rod may include an outer cylinder coupled to the aircraft structure, a piston located at least partially within the outer cylinder and coupled to the interior aircraft monument, and a compressed gas located in a volume defined by the piston and the outer cylinder.

An aircraft having an augmented reality flight control system integrated with and operable from the pilot seat and an associated pilot headgear unit, wherein the flight control system is supplemented by flight-assisting artificial intelligence and geo-location systems is presented. The present disclosure includes an augmented reality flight control system incorporating real-world objects with virtual elements to provide relevant data to a pilot during aircraft flight. A translucent substrate is disposed in the pilot's field of view such that the pilot can see therethrough, and observe virtual elements displayed on the substrate. The system includes a headgear that is worn by the pilot. A flight assistance module is configured to receive data related to the aircraft and provide predictive assistance to the pilot during flight based on the received data based in part on a pilot profile having preferences related to the pilot.

A wall assembly for an interior of an aircraft includes a frame member secured within a cabin of the aircraft having a first side and a second opposing side. The assembly further includes a first decorative panel secured to the frame member on a first side of the frame and a second decorative panel secured to the frame member on a second side of the frame.

A tolerance-compensating fastening arrangement for fastening a component to a structure includes a male fastener having a fastening bolt having a serrated outer profile; and a female fastener having a socket base arranged therewithin movable along a horizontal plane and having a conical funnel to receive the bolt such that horizontal tolerances between the male and female fasteners are compensable by movement of the socket base actuated through contact of the bolt with an inner surface of the funnel; and a socket jaw arranged on the socket base and having several jaw segments arranged circumferentially around a vertical axis to form a central jaw opening configured to receive the bolt through the funnel, the jaw segments configured movable radially with respect to the vertical axis to adjust a size of the jaw opening to retain the bolt along the vertical axis via contact of the serrated inner and outer profiles.

A low heat release veneer product for aircraft interior components may include at least one substrate layer, at least one thermally-conductive layer disposed on the at least one substrate layer, at least one veneer layer disposed on the at least one thermally-conductive layer, and at least one coating disposed on the at least one veneer layer. One or more of the at least one substrate layer, the at least one thermally-conductive layer, the at least one veneer layer, or the at least one coating may be compliant with an OSU 65/65 rate of heat release test.

The present invention achieves technical advantages as a vehicle cabin, comprising a floor system formed of removable and reconfigurable floor segments extending from a vehicle frame, and a ceiling system formed of removable and reconfigurable ceiling segments disposed in the ceiling of the vehicle cabin. Floor segments that can be positioned to form a floor channel, therebetween. A fixture interface adapted to releasably secure a fixture to the floor system. The fixture can be slidably repositioned within the vehicle along the floor channel. One of the ceiling segments includes one or more of a lighting module, a ventilation outlet, a ventilation inlet, a display screen, or a touch control panel. The ceiling segments can be hexagonal.