Abstract: The invention relates to a method for producing a plastic foil tube with an intended cross-section that derives from a circular cross-section as a means for the production of fiber compound components for aviation or aerospace. It comprises the following method steps: mounting a semi-finished tube on a core tool; charging the mounted semi-finished tube with a predetermined force to press the semi-finished tube on a core cross section of the core tool, wherein while charging the mounted semi-finished tube with the force crinkles are formed in longitudinal direction of the semi-finished tube; heating the semi-finished tube to a predetermined forming temperature for a predetermined time period for the production of the plastic foil tube with the intended cross-section and stripping the plastic foil tube which is formed in such a manner and cooled down off the core tool.

Abstract: A method for producing an integral reinforced fiber composite component comprising at least one hollow fiber reinforcing component and a shell component is disclosed and can include first providing a mold core having a target cross-section deviating from a round cross-section adaptable to an inner cross-section of the hollow reinforcing component, introducing the mold core into a cavity of the hollow reinforcing component and fixing it thereafter in the cavity with a fixing agent applying the hollow reinforcing component with the mold core fixed therein to the shell component, and subjecting the mold core to a pressurized medium while applying heat and/or pressure to this arrangement to produce the integral reinforced fiber composite component.

Abstract: A method and an arrangement for reinforcing a fibre composite component for the aviation and aerospace industry, in which a reinforcing element having a receiving region and a pressure element adapted to the receiving region geometry. The pressure element is inserted into the reinforcing element receiving region. The reinforcing element and the inserted pressure element are fastened relative to one another in a reproducible manner by a reversible fastening device. The fastening device includes a first fastening portion mounted on the pressure element and a second fastening portion which can be mounted on the reinforcing element. The reinforcing element, with the pressure element, is then applied in a reproducible manner to the fibre composite component to be reinforced, to form a moulding portion. The formed moulding portion is cured to connect the reinforcing element to the fibre composite component. The fastening device and the pressure element are then removed from the fibre composite component.

Abstract: A device for the master moulding technique production of an integral structural component made of a fibre composite for an aircraft that is reinforced by stringers includes at least one moulded part forming a mounting surface to create an exterior or interior surface of the structural component, onto which at least one channel for evacuation of the structural component covered by a vacuum film is arranged, with the structural component comprising a skin-like laminate and a plurality of stringers which are disposed spaced apart from one another, wherein at least surface sections between adjacent stringers are covered with an auxiliary stripe, which comprises a textile ventilation fleece which rests on a vacuum film, and a pre-assembled release film firmly connected therewith, the width (BF) of which is greater than or equal to the width (BV) of the ventilation fleece.

Abstract: The invention relates to a method for producing a plastic foil tube with an intended cross-section that derives from a circular cross-section as a means for the production of fiber compound components for aviation or aerospace. It comprises the following method steps: mounting a semi-finished tube on a core tool; charging the mounted semi-finished tube with a predetermined force to press the semi-finished tube on a core cross section of the core tool, wherein while charging the mounted semi-finished tube with the force crinkles are formed in longitudinal direction of the semi-finished tube; heating the semi-finished tube to a predetermined forming temperature for a predetermined time period for the production of the plastic foil tube with the intended cross-section and stripping the plastic foil tube which is formed in such a manner and cooled down off the core tool.

Abstract: The invention relates to a method for producing an integral, reinforced fibre composite component comprising at least one hollow reinforcing component made of fibre composite material and shell component, comprising the following method steps: providing a mould core formed of a hose having a target cross-section deviating from a round cross-section and is adapted to an inner cross-section of the hollow reinforcing component to be produced, at least in portions, or substantially corresponds with said inner cross-section, at least in portions; introducing the mould core into a cavity in the at least one hollow reinforcing component; fixing the mould core in the at least one hollow reinforcing component using a fixing agent; applying the at least one hollow reinforcing component with the mould core fixed therein to the shell component; and subjecting the mould core to a pressurised medium and applying heat and/or pressure to this arrangement in order to produce the integral, reinforced fibre composite component