A wall covering panel for a nose of an aircraft. The panel comprises a rigid carrying framework preferably having an alveolar structure obtained by 3-D printing, a décor carried by the carrying framework and an acoustically and thermally insulating padding fixed to the carrying framework, and also attachments for fixing the carrying framework to the primary structure of the aircraft. Preferably, the panel also integrates systems, such as electrical route portions or ventilation route portions that traverse the panel from one side to the other or lead to an outlet equipment item also integrated in the panel. Only the carrying structure of the panel, which carries the décor, the insulating padding and any route portions and equipment items, is fixed to the primary structure of the aircraft. The number of attachments is low; the kitting-out and the finishing of the nose of the aircraft are greatly simplified.

A retaining assembly and method for use within an internal cabin of an aircraft, in which the retaining assembly includes a hinge including a biasing member. The hinge is moveable between a retaining position, in which the biasing member is configured to exert a biasing force into a top surface of a ceiling panel within an internal cabin of a vehicle to prevent the ceiling panel from upward motion, and a release position, in which the hinge is configured to be pivoted away from the ceiling panel and the biasing member is configured to be separated from the ceiling panel.

An internal cladding part for cladding a fuselage structure of an aircraft is disclosed having a first cover layer that extends in a planar manner, a second cover layer that extends in a planar manner, a core layer which is disposed between the first and the second cover layer and is connected to the first and the second cover layer and defines a receptacle cavity, and an insulation structure having a porous insulation core and an evacuated film sheath that encases the insulation core in a gas-tight manner. The insulation structure is disposed in the receptacle cavity between the first and the second cover layer.

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.

In summary, the present application relates to an aircraft interior paneling (10) comprising:—a planar replaceable surface element (40);—a structural element (20);—at least one connection element (30); wherein the replaceable surface element (40) is detachably fastened to the structural element (20) by means of the at least one connection element (30), and wherein the replaceable surface element (40) comprises:—a support element (42), wherein, in the thickness direction of the support element (42), the support element (42) comprises a plurality of successive layers which comprise woven fabrics;—a decorative element (50) which is attached to a decorative connection surface (52) of the support element (42), wherein the support element (42) is dimensionally stable; and a replaceable surface element (40) for an aircraft interior paneling (10); the use of a replaceable surface element (40) for an aircraft interior paneling (10); a method for producing a replaceable surface element (40) for an aircraft interior paneling (10); and a method for updating an existing aircraft interior paneling (100).

A panel assembly for an overhead support structure of a vehicle. The panel assembly includes a panel movable relative to the overhead support structure between a stowed position and an open position. One or more actuators release the panel from the stowed position. The actuators include first and second bodies arranged together and configured to move relative to each other and with the first body movable relative to the overhead support structure between first and second positions. The first position orients the second body at a first angular position relative to the overhead support structure that engages a catch on the second body with a latch pin. The second position orients the second body at a different second angular position relative to the overhead support structure to release the catch from the latch pin and thereby release the panel from the stowed position.

Interior panels for an interior of a vehicle, vehicles, and methods for making interior panels for an interior of a vehicle are provided. In one example, the interior panel includes an outer covering having a first surface exposed to the interior and a second surface disposed opposite the first surface. The second surface has a pattern formed therein that is covered by the first surface. A board assembly is disposed proximate the second surface and has a third surface facing towards the second surface. The board assembly includes a light source that is generally aligned with the pattern. An adhesive layer is disposed between the second surface and the third surface and couples the second surface and the third surface together. When the light source generates light, the light passes through the adhesive layer and the pattern to produce an illuminated pattern on the first surface.

The aim of the invention is to propose an edging method that is quick, effective, easy to implement and makes it possible to obtain a lightweight panel. To this end, the aim of the invention is a method for sealingly edging a composite panel comprising; *a step (a) of providing a composite panel of redefined thickness having two planar faces and a side to be edged, and of providing a sealing strip made from a polymer material having a width greater than the thickness of the composite panel, and comprising a first face, referred to as the “inner” face, and a second face, referred to as the “outer” face, in reference to the position of use of same: *a step (b) of applying the strip and an adhesive to the side and to a peripheral portion of the planar faces of the composite panel in such a way that the adhesive is located between the composite panel and the inner face of the strip, which sealingly protects the composite panel against dust, foreign bodies and the absorption of moisture.

A fixation assembly for affixing a first object to and variably spaced from a second object. The assembly comprises a male fastener and a female fastener. The male fastener comprises a bolt-shaped part having a circumferential outer surface. The surface includes alternately on a circumferential path, in a cross-sectional plane of the part, at least one ridged section and at least one plain section. The female fastener comprises a tubular part having a circumferential inner surface. The inner surface includes alternately on a circumferential path, in a cross-sectional plane of the part, at least one ridged section and at least one plain section. The male fastener can be inserted into the female fastener such that its ridged section coincides with the female fastener plain section. Either the male or female fastener is configured to be rotated relative to the other, thereby engaging respective ridges of the two fasteners.

A decompression panel assembly for use in an aircraft includes a frame including a first surface and an opposing second surface, wherein the frame defines a grille opening and at least partially defines a flow path opening. The decompression panel assembly also includes a face panel having a first surface retained against the frame second surface such that the face panel at least partially covers the grille opening. A retention mechanism is coupled to the face panel and is configured to retain the face panel against the frame in a closed position.