Process for forming a permanent join between two sections of fibrous material contained in a thermosetting resin matrix, said process comprising overlaying the two sections and subjecting the overlaid sections to ultrasonic welding to form a permanent join between the two sections, wherein there is no significant change in the sub-ambient Tg of the fibrous material contained in the thermosetting resin matrix in the region of the permanent join.

Various embodiments may include a method for making a gas separator for use in electrochemical conversion processes comprising: mixing an inorganic fiber into a solution to form a casting suspension, wherein the solution comprises an organic binding material as a solute and a solvent for the solute; spreading the casting suspension on an inert surface to form a sheet; and extracting the solvent from the sheet to form the gas separator.

The present invention relates to a process for producing a fiber-foam composite (FSV1), wherein a first fiber material (FM1) is applied to a first foam body (SK1) to give a first structured fiber surface (FO1) to which a second foam body (SK2) is subsequently applied to give the fiber-foam composite (FSV1).

The present invention relates to a process for producing a fiber-foam composite (FSV1), wherein a first fiber material (FM1) is applied to a first foam body (SK1) to give a first structured fiber surface (FO1) to which a second foam body (SK2) is subsequently applied to give the fiber-foam composite (FSV1).

A method for producing a frame component for a door frame structure of an aircraft. A connecting zone is generated on a first and a second assembly surface of a connecting component in each case by generating a surface texture on the assembly surfaces, wherein the connecting component is formed from a metal material. The assembly surfaces of the connecting component are placed against a door frame member and against an attachment member, wherein the door frame member and the attachment member are each formed from a fiber-reinforced thermoplastics material. Furthermore, the connecting component and the door frame member are welded, and the connecting component and the attachment member are welded. A frame component and a door frame structure are also described.

A method for producing a frame component for a door frame structure of an aircraft. A connecting zone is generated on a first and a second assembly surface of a connecting component in each case by generating a surface texture on the assembly surfaces, wherein the connecting component is formed from a metal material. The assembly surfaces of the connecting component are placed against a door frame member and against an attachment member, wherein the door frame member and the attachment member are each formed from a fiber-reinforced thermoplastics material. Furthermore, the connecting component and the door frame member are welded, and the connecting component and the attachment member are welded. A frame component and a door frame structure are also described.

A pressure tool for applying a pressure force during the welding of plastics components has at least one metallic first component contact section, wherein the pressure tool has at least one elastically deformable second component contact section and is thermally controllable. A Pressure apparatus has at least one such pressure tool for pressing together plastics components during welding. A method for welding plastics components is carried out by such a pressure apparatus and plastics module having at least two welded-together plastics components, wherein the at least two plastics components are welded using such a method.

A pressure tool for applying a pressure force during the welding of plastics components has at least one metallic first component contact section, wherein the pressure tool has at least one elastically deformable second component contact section and is thermally controllable. A Pressure apparatus has at least one such pressure tool for pressing together plastics components during welding. A method for welding plastics components is carried out by such a pressure apparatus and plastics module having at least two welded-together plastics components, wherein the at least two plastics components are welded using such a method.

This pertains to a method for connecting fiber-reinforced structural components. In a first step of the method, a first fiber-reinforced structural component and a second fiber-reinforced structural component are supplied. In another step, the first fiber-reinforced structural component and the second fiber-reinforced structural component are heated by means of a heating device. A penetration through the first fiber-reinforced structural component and the second fiber-reinforced structural component is produced in another step by means of a fastening device. In another step, the first fiber-reinforced structural component is connected to the second fiber-reinforced structural component by means of the fastening device. This furthermore pertains to a structural aircraft element.

This pertains to a method for connecting fiber-reinforced structural components. In a first step of the method, a first fiber-reinforced structural component and a second fiber-reinforced structural component are supplied. In another step, the first fiber-reinforced structural component and the second fiber-reinforced structural component are heated by means of a heating device. A penetration through the first fiber-reinforced structural component and the second fiber-reinforced structural component is produced in another step by means of a fastening device. In another step, the first fiber-reinforced structural component is connected to the second fiber-reinforced structural component by means of the fastening device. This furthermore pertains to a structural aircraft element.