The present disclosure relates to a method of molding a motor vehicle part, the motor vehicle part being made from thermosetting plastic material and including at least one metal insert having a shape allowing it to extend substantially through the entire thickness of the motor vehicle part, the method being characterized in that it includes the following steps placing the metal insert and the thermosetting plastic material in a mold, and molding the motor vehicle part comprising the overmolded metal insert, the metal insert being deformed at least at one mechanical weakening zone by closing the mold for molding the motor vehicle part.

A pivoting fastener assembly for securely fastening a panel in spaced relation to a support backing, and a method of manufacturing the same. The fastener assembly includes: a magnet-carrier assembly that includes a magnet that is fixed to a carrier member; and a base member that includes a base portion and a pivoting portion. The pivoting portion includes a head, a trunk, and an extension portion that is connected to the base portion. The extension portion includes a top side that connects a first peripheral surface to a second peripheral surface of the extension portion. A first end of the trunk is connected to the top side of the extension portion and a second end of the trunk is connected to the head. The base member is a unitary piece, and the head of the pivoting portion engages and retains the carrier member of the magnet-carrier assembly.

A pivoting fastener assembly for securely fastening a panel in spaced relation to a support backing, and a method of manufacturing the same. The fastener assembly includes: a magnet-carrier assembly that includes a magnet that is fixed to a carrier member; and a base member that includes a base portion and a pivoting portion. The pivoting portion includes a head, a trunk, and an extension portion that is connected to the base portion. The extension portion includes a top side that connects a first peripheral surface to a second peripheral surface of the extension portion. A first end of the trunk is connected to the top side of the extension portion and a second end of the trunk is connected to the head. The base member is a unitary piece, and the head of the pivoting portion engages and retains the carrier member of the magnet-carrier assembly.

A lightning strike protection layer for an aircraft is disclosed having a first portion and a second portion, the first portion includes a first fibre reinforced polymer composite layer and a first electrically conductive metal layer and the second portion includes a second fibre reinforced polymer composite layer and a second electrically conductive metal layer, and the first and second portions are joined at a butt joint, with the first and second fibre reinforced polymer composite layers abutting and the first and second electrically conductive metal layers abutting; and a butt-strap extending across the butt joint, the butt-strap comprising a third electrically conductive metal layer electrically connected to the first and second electrically conductive metal layers.

An assembly (113) for composite manufacture is provided. The assembly comprises a cured resin impregnated reinforcement material (112) comprising a fibre component and a resin matrix component, in which the resin matrix component comprises polyurethane, the assembly having a length to width ratio of at least 5:1, and the assembly defining a longitudinal direction (L) along its length; and a peel ply (116) in contact with the cured resin impregnated reinforcement material (112), the peel ply (116) comprising a woven layer having a plurality of longitudinal fibres (118) extending in the longitudinal direction (L); and a plurality of transverse fibres (120) extending in a transverse direction (T) normal to the longitudinal direction (L); in which the areal density of the plurality of transverse fibres (120) is higher than the areal density of the plurality of longitudinal fibres (118).

A functionally gradient material for guided periodontal hard and soft tissue regeneration includes a 3D printed scaffold layer and an electrospun fibrous membrane layer. The content of hydroxyapatite in the 3D printed scaffold layer is higher than the content of hydroxyapatite in the electrospun fibrous membrane layer. The pore size of the 3D printed scaffold layer is larger than the pore size of the electrospun fibrous membrane layer. The pore size of the 3D printed scaffold layer is 100-1000 μm, and the fiber diameter of the electrospun fibrous membrane layer is 300-5000 nm. The electrospun fibrous membrane layer is in a random distribution or an oriented arrangement or has a mesh structure. The thickness of the electrospun fibrous membrane layer is 0.08-1 mm.

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.

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 system and method for manufacturing composite parts has been developed which offers the ability to produce composite parts in an infusion resin process without the use of expensive preforms or tools. In addition, the methods of manufacturing composite parts described herein offer the ability to produce composite parts having complex structures without the need for complex tooling. The method of manufacturing and systems described herein typically include printing a part skeleton using an additive manufacturing process followed by infusing the part skeleton with resin and curing the resin infused part skeleton to form the composite part.

Joiners, methods of joining, and related systems for additive manufacturing are provided. The method of joining includes bulk depositing, by an additive manufacturing tool head, a joiner (anchor) of a second material in a receptacle in a body of a first material. Also, the method of joining includes depositing an anchor layer of a third material upon the anchor. Networks of joiners in 3D printed parts, multi-material parts comprising joiners, computer program products for providing joiners, joiner systems including trolleys, and related methods and systems are also provided. Further provided is a system, and method, for securing a part to a build platform and separating the part from the build platform.