A method for welding thermoplastic components, in particular, thermoplastic fiber composite structural components for an aircraft or spacecraft, having the following steps. Arranging an insert, which has a conductor structure having a plurality of parallel electrical conductor elements, in a joining zone between a first thermoplastic component and a second thermoplastic component such that at least some portions of the parallel electrical conductor elements are located in the joining zone; locally melting the components in the region of the joining zone by supplying current to the conductor structure; disconnecting the connector elements; and removing the insert from the joining zone by pulling out the disconnected conductor elements. An insert for the resistance welding of thermoplastic components is also provided.

A thermoplastic composite structure is produced by consolidating and forming a composite preform to a desired shape. The preform comprises plies of a high melt temperature thermoplastic prepreg that are tacked together by a low melt temperature thermoplastic adhering the plies together in fixed registration.

A thermoplastic composite structure is produced by consolidating and forming a composite preform to a desired shape. The preform comprises plies of a high melt temperature thermoplastic prepreg that are tacked together by a low melt temperature thermoplastic adhering the plies together in fixed registration.

A printhead a supplying portion with a supplying opening of a filament; a melting portion to melt a filament supplied; a discharging portion having a discharging opening to discharge the melted filament. A heat insulating portion between the supplying portion and the melting portion are integrally formed to effectively suppress heat in the melting portion conducting to the supplying portion even when the melting portion is heated to high temperature, to maintain the temperature of the supplying portion to an appropriate temperature, and to efficiently utilize heat by the melting portion as a result of heating the melting portion.

A method for joining two objects by anchoring an insert portion provided on one of the objects in an opening provided on the other one of the objects. The anchorage is achieved by liquefaction of a thermoplastic material and interpenetration of the liquefied material and a penetrable material, the two materials being arranged on opposite surfaces of the insert portion and the wall of the opening. Before such liquefaction and interpenetration, an interference fit is established in which such opposite surfaces are pressed against each other, and, for the anchoring, mechanical vibration energy and possibly a shearing force are applied, wherein the shearing force puts a shear stress on the interference fit.

A method for joining two objects by anchoring an insert portion provided on one of the objects in an opening provided on the other one of the objects. The anchorage is achieved by liquefaction of a thermoplastic material and interpenetration of the liquefied material and a penetrable material, the two materials being arranged on opposite surfaces of the insert portion and the wall of the opening. Before such liquefaction and interpenetration, an interference fit is established in which such opposite surfaces are pressed against each other, and, for the anchoring, mechanical vibration energy and possibly a shearing force are applied, wherein the shearing force puts a shear stress on the interference fit.

A method for forming a composite part of a gas turbine engine. The method includes assembling the composite part of a first composite material and a second composite material. The second composite material defines an outer surface of the composite part, and is selected to be curable at a cure temperature generated by heat from operation of the engine. The first composite material is selected to have an operating temperature limit less than the cure temperature. The method includes placing the composite part within the engine so that, in use, the second composite material is cured by exposure to the heat generated from operation of the engine. The second composite material thermally shields the first composite material from the heat generated from operation of the engine. The method includes operating the engine to cure the second composite material.

A method for forming a composite part of a gas turbine engine. The method includes assembling the composite part of a first composite material and a second composite material. The second composite material defines an outer surface of the composite part, and is selected to be curable at a cure temperature generated by heat from operation of the engine. The first composite material is selected to have an operating temperature limit less than the cure temperature. The method includes placing the composite part within the engine so that, in use, the second composite material is cured by exposure to the heat generated from operation of the engine. The second composite material thermally shields the first composite material from the heat generated from operation of the engine. The method includes operating the engine to cure the second composite material.

The present disclosure provides tissue wrap devices with embedded three dimensional attachment features, methods of manufacturing three-dimensional attachment features for tissue wrap devices, and methods of using a nerve wrap device to protect a damaged nerve. Tissue wrap devices of the present disclosure may include a sheet of biocompatible material, the sheet having a first side, a second side, a middle portion, a first outer portion, and a second outer portion, the first side of the first outer portion being configured to overlap and interface with the second side of the second outer portion when the sheet is transitioned to a rolled configuration; wherein the first side of the first outer portion comprises a plurality of three dimensional attachment features; and wherein the plurality of three dimensional attachment features are configured to engage with the second side of the second outer portion to maintain the sheet in the rolled configuration.

The invention relates to a process for preparing polymeric particles, based on the use of a polyester polymer (PE) comprising units from a dicarboxylic acid component and a diol component, wherein at least 2 mol. % of the diol component is a poly(alkylene glycol). The process comprises the melt-blending of the aromatic polymer (P) with the PE, the cooling the blend and the recovery of the particles by dissolution of the PE into water. The present invention relates to polymeric particles obtained therefrom and to the use of these particles in SLS 3D printing, coatings and toughening of thermoset resins.