The invention relates to a shaping device (10), which comprises an inductor (14) and one or more shaping half-shells (12, 34), wherein at least one shaping half-shell (12, 34) comprises a bottom shaping element (16) produced from mineral material, and a top shaping element (17), wherein the top shaping element (17) is releasably connected to the bottom shaping element (16) or is formed integrally with it, covers at least parts of an inner surface (16a) of the bottom shaping element (16) and comprises an electrically conductive layer (18), and the inductor (14) is designed to induce eddy currents in the electrically conductive layer (18). The invention further relates to a shaping mould (40) with a part to be formed (38), as well as to a method for heating a shaping surface (17a) of a top shaping element (17) of a shaping half-shell (12, 34) or a shaping surface (38a) of a part to be formed (38).

A method of forming a structural composite is disclosed. The method comprises combining an uncured resin and a carbon fiber textile to form a first layer. The method also comprises forming a second layer comprising uncured concrete adjacent the first layer, wherein the uncured concrete of the second layer is in contact with the uncured resin of the first layer. Finally, the method comprises curing the first and second layers, thereby forming the structural composite. A structural composite produced by the above method is also disclosed.

The invention relates to a method for joining fiber-plastic composite (FPC) components, in particular aircraft FPC components, comprising the following steps: i) providing a first and a second FPC component, the first FPC component having a recess; ii) introducing a stabilizing device into the recess of the first FPC component, the stabilizing device having a basic body with a cavity, an opening and a pressing element, which pressing element has at least partially a higher flexibility than the base body; iii) filling the cavity with a fluid, so that the pressing element is pressed against a delimiting surface of the first FPC component, which delimits the recess; iv) connecting the first FPC component to the second FPC component by joining at a connecting point, wherein a pressure force, is exerted onto the connecting point by means of the pressing element for stabilizing the form of the recess.

The invention relates to a method for joining fiber-plastic composite (FPC) components, in particular aircraft FPC components, comprising the following steps: i) providing a first and a second FPC component, the first FPC component having a recess; ii) introducing a stabilizing device into the recess of the first FPC component, the stabilizing device having a basic body with a cavity, an opening and a pressing element, which pressing element has at least partially a higher flexibility than the base body; iii) filling the cavity with a fluid, so that the pressing element is pressed against a delimiting surface of the first FPC component, which delimits the recess; iv) connecting the first FPC component to the second FPC component by joining at a connecting point, wherein a pressure force, is exerted onto the connecting point by means of the pressing element for stabilizing the form of the recess.

A heating device to heat a molding face, particularly a large molding face. The heating device includes a metal sheet having a ferromagnetic layer, and a part formed into a shape that defines the molding face and a forming plane. A base of the heating device supports the metal sheet. An inductor of the heating device provides the induction heating of the metal sheet.

An inorganic composite, the use of the inorganic composite in tools and molds, a mechanical forming tool, a mold, and a process for manufacturing inorganic composite tools and molds. The composite material mold and/or mechanical forming tool, metal forming, casting or injection mold, said molds or tools have physicochemical properties. The manufacturing process provides fast, low-cost, high-quality manufacture and reduced energy and raw material consumption, making industrial production economically feasible by forming of structural composite materials and bringing environmental advantages.

A heating device to heat a molding face, particularly a large molding face. The heating device includes a metal sheet having a ferromagnetic layer, and a part formed into a shape that defines the molding face and a forming plane. A base of the heating device supports the metal sheet. An inductor of the heating device provides the induction heating of the metal sheet.

The invention relates to a method for joining fiber-plastic composite (FPC) components, in particular aircraft FPC components, comprising the following steps: i) providing a first and a second FPC component, the first FPC component having a recess; ii) introducing a stabilizing device into the recess of the first FPC component, the stabilizing device having a basic body with a cavity, an opening and a pressing element, which pressing element has at least partially a higher flexibility than the base body; iii) filling the cavity with a fluid, so that the pressing element is pressed against a delimiting surface of the first FPC component, which delimits the recess; iv) connecting the first FPC component to the second FPC component by joining at a connecting point, wherein a pressure force, is exerted onto the connecting point by means of the pressing element for stabilizing the form of the recess.

The invention relates to a method for joining fiber-plastic composite (FPC) components, in particular aircraft FPC components, comprising the following steps: i) providing a first and a second FPC component, the first FPC component having a recess; ii) introducing a stabilizing device into the recess of the first FPC component, the stabilizing device having a basic body with a cavity, an opening and a pressing element, which pressing element has at least partially a higher flexibility than the base body; iii) filling the cavity with a fluid, so that the pressing element is pressed against a delimiting surface of the first FPC component, which delimits the recess; iv) connecting the first FPC component to the second FPC component by joining at a connecting point, wherein a pressure force, is exerted onto the connecting point by means of the pressing element for stabilizing the form of the recess.