An inflatable suspended ceiling for a vehicle compartment, in particular for a passenger cabin of an aircraft, includes a flat fabric cover sheet configured to roof over at least a longitudinal section of an interior space along an extending direction of the vehicle compartment underneath a structural ceiling of the vehicle compartment, and a tensioning structure attached to the cover sheet to carry the cover sheet from above and having a flexible envelope enclosing at least one inflatable chamber configured to tension the cover sheet when inflated. Mounting members are attached to the tensioning structure to mount the tensioning structure to counter-mounting members on the structural ceiling in a hanged configuration.

A compound contour vacuum track, and an automated fastening machine using the track, for automation of final assembly inside an aircraft fuselage. The track is mounted at an angle to a surface, such as an inside surface of the fuselage, wherein the surface has one or more holes through which fasteners are inserted. The automated fastening machine is mounted on the track to traverse the track while performing fastening functions and steps. The automated fastening machine includes a carriage, arm, and end effector, wherein the arm is mounted on the carriage and the end effector is mounted on the arm. The carriage is attached to the track for positioning the arm and end effector, the arm is attached to the carriage for positioning the end effector, and the end effector is attached to the arm for installing the fasteners into the holes of the surface.

A component system for an aircraft, having at least one furnishing component, a plurality of component rails, a plurality of guide elements engageable with and movable relative to the component rails, a plurality of retaining elements connected to the guide elements and configured to be coupled to a hull structure of the aircraft or the at least one furnishing component, and a plurality of locking units arranged on the component rails and/or on the guide elements and configured to lock the guide elements to a particular rail. At least two component rails are arranged on the at least one furnishing component or the hull structure at a distance and parallel to each other such that the furnishing component is retractable via the component rails on guide elements or component rails that are spatially fixed in the aircraft and can be locked in a retracted position by the locking units.

A method for producing a panel with integrated conductor tracks and electronic components. The panel includes a panel body, wherein the panel body is in particular a sandwich structure, and a membrane. The membrane is connected to the panel body and has integrated conductor tracks and electronic components. At the beginning of the method, an operation for attaching the conductor tracks and the electronic components to the membrane is provided. The subsequent step includes an operation for connecting the membrane, fitted with the conductor tracks and the electronic components, to the panel body.

A cargo hold of an aircraft having cladding elements and at least one housing element for accommodating electronic components and/or cables. The cladding elements are attached to supports, in particular structural elements, of the aircraft and have a plurality of cladding holes with predefined cladding hole spacings for attachment. The at least one housing element has at least one pair of housing holes for receiving fastening devices. The housing holes have a housing hole spacing which corresponds to at least one pair of cladding hole spacings.

An acoustic attenuation structure includes a periodic structure having a first unit cell, the first unit cell having a first central body and a first axial tube disposed on the first central body and a second axial tube disposed on the first central body, opposite the first axial tube, each of the first axial tube and the second axial tube being in fluid communication with one another through the first central body.

A quick attach bracket includes a first portion and a second portion aligned substantially perpendicular with the first portion, a retaining ridge disposed across the first portion and extending in the direction of the second portion, and a hub disposed on the second portion and extending in the direction of the first portion. The retaining ridge is configured to receive a flange of a structure. The hub includes a sidewall that extends from the second portion in the direction of the first portion, a façade aligned with the second portion, and a rounded portion connecting the sidewall and the façade to assist with installation of the hub into a recess or through-hole of the structure. The quick attach bracket is installable by hand via hooking of the retaining ridge on the flange and insertion of the hub into the recess or through-hole.

A decorative laminate is disclosed, including a first laminate layer containing an anti-microbial agent and a second laminate layer. A decorative layer is disposed selectively between the first laminate layer and the second laminate layer. The first and second laminate layers include a thermoplastic fluoropolymer material. The first laminate layer, the decorative layer, and the second laminate layer are laminated together to form the decorative laminate, which is configured for application to a structural component.

A panel (1000) for a cabin of an aircraft, the panel (1000) including a laminate (150) with a first layer formed of lithiated carbon fibers (100), a second layer form of carbon fibers with a cathode lithium coating (200), and an electrolyte-containing separator (300) interposed between the first and the second layers and a pressure sensor (50a, 50b) on an outer surface of the laminate (150), and a switch (40) to regulate a voltage to the laminate (150) based on an output of the pressure sensor (50a, 50b) so that the panel (1000) expands.

An assembly to connect a panel to a support member. The assembly may include a saddle fitting configured to connect to the support member and including first and second plates. A back fitting may be positioned between the second plate of the saddle fitting and a second face of the panel. An index fitting includes a flange that may be positioned between the first plate of the saddle fitting and a first face of the panel, and a boss that extends outward from the flange and through the opening in the panel. The index fitting is wider than the panel and sized to fit within the gap of the saddle fitting with a first end of the index fitting contacting against the first plate and a second end of the index fitting contacting against the second plate. One or more fasteners may connect the saddle fitting to the index fitting.