A manufacturing method for manufacturing a welded thermoplastic composite and honeycomb core structure is provided. A thermoplastic composite and honeycomb structure is generated by positioning a first thermoplastic composite skin on a support structure, positioning a first thermoplastic film over the first thermoplastic composite skin, positioning a honeycomb core over the first thermoplastic film, positioning a second thermoplastic film is positioned over the honeycomb core, and positioning a second thermoplastic composite skin over the second thermoplastic film. The second thermoplastic composite skin is ultrasonically welded to the honeycomb core. The thermoplastic composite and honeycomb structure is then flipped over, and the first thermoplastic composite skin is then ultrasonically welded to the honeycomb core.

A method of joining a first element in composite material with a second element in composite material to define a structural component of an aircraft comprising arranging the first element in contact on the second element; applying a non-rigid heating layer on the first element; applying a layer of shape memory thermoplastic polymer, pre-loaded in a compressed non-equilibrium condition, onto the heating layer; applying a vacuum bag to the assembly thus obtained; sealing the vacuum bag to define a vacuum chamber housing the first element, at least part of the second element, the heating layer and the shape memory layer; applying vacuum inside the vacuum chamber; applying heat to the first element, to the second element and to the shape memory layer by activating the heating layer; expanding the shape memory layer from the compressed non-equilibrium condition to an expanded equilibrium condition by means of the step of applying heat.

A method of joining a first element in composite material with a second element in composite material to define a structural component of an aircraft comprising arranging the first element in contact on the second element; applying a non-rigid heating layer on the first element; applying a layer of shape memory thermoplastic polymer, pre-loaded in a compressed non-equilibrium condition, onto the heating layer; applying a vacuum bag to the assembly thus obtained; sealing the vacuum bag to define a vacuum chamber housing the first element, at least part of the second element, the heating layer and the shape memory layer; applying vacuum inside the vacuum chamber; applying heat to the first element, to the second element and to the shape memory layer by activating the heating layer; expanding the shape memory layer from the compressed non-equilibrium condition to an expanded equilibrium condition by means of the step of applying heat.

The invention pertains to a composite part with a fibrous reinforcement and a thermoplastic polymer matrix, comprising: substrate part with a matrix of a first thermoplastic polymer having a first melting temperature; stiffener made of a composite material with a matrix of a second thermoplastic polymer having a second melting temperature; comprising the steps of: obtaining an unconsolidated preform of the substrate part; obtaining a preform of the stiffener; integrating a layer of the first thermoplastic polymer into the preform of the stiffener at a location configured to be in contact with the substrate part; and subjecting the substrate part and the preform of stiffener to a thermomechanical cycle so as to consolidate the substrate part and weld the stiffener to the substrate part.

The invention pertains to a composite part with a fibrous reinforcement and a thermoplastic polymer matrix, comprising: substrate part with a matrix of a first thermoplastic polymer having a first melting temperature; stiffener made of a composite material with a matrix of a second thermoplastic polymer having a second melting temperature; comprising the steps of: obtaining an unconsolidated preform of the substrate part; obtaining a preform of the stiffener; integrating a layer of the first thermoplastic polymer into the preform of the stiffener at a location configured to be in contact with the substrate part; and subjecting the substrate part and the preform of stiffener to a thermomechanical cycle so as to consolidate the substrate part and weld the stiffener to the substrate part.

A personal protective vest assembly is described herein. The personal protective vest assembly includes a personal protective vest and a body armor panel positioned within the personal protective vest. The body armor panel includes a ballistic material panel assembly that includes a plurality of layered material segments defined between a strike face and a wear face. Each of the layered material segments includes a different ballistic material.

A personal protective vest assembly is described herein. The personal protective vest assembly includes a personal protective vest and a body armor panel positioned within the personal protective vest. The body armor panel includes a ballistic material panel assembly that includes a plurality of layered material segments defined between a strike face and a wear face. Each of the layered material segments includes a different ballistic material.

A trim part, in particular for covering an airbag in a vehicle, is provided. The trim part comprises at least one outer layer, at least one hinge layer comprising at least one first break line which forms a first part of a perimeter of a flap area and is attached to a first surface of the at least one outer layer, at least one structural layer attached to a first surface of the at least one hinge layer facing away from the at least one outer layer characterized in that at least one of the at least one outer layer comprises a fiber composite material and the at least one structural layer comprises at least one second break line forming a breakthrough area corresponding to the flap area of the at least one hinge layer.

A repair method is provided during which a thermoplastic patch is arranged on a thermoplastic aerospace component. An ultrasonic horn is arranged on the thermoplastic patch. The thermoplastic patch is vertically between the thermoplastic aerospace component and the ultrasonic horn. The thermoplastic patch contacts the ultrasonic horn. The thermoplastic patch is continuous ultrasonic welded to the thermoplastic aerospace component using the ultrasonic horn.

A repair method is provided during which a thermoplastic patch is arranged on a thermoplastic aerospace component. An ultrasonic horn is arranged on the thermoplastic patch. The thermoplastic patch is vertically between the thermoplastic aerospace component and the ultrasonic horn. The thermoplastic patch contacts the ultrasonic horn. The thermoplastic patch is continuous ultrasonic welded to the thermoplastic aerospace component using the ultrasonic horn.