Abstract: A reinforcing element for a structural profile, in particular for a round, oval or elliptical structural tube. The reinforcing element comprises: a fiber structure which has a hollow-cylindrical, helically wound mesh of fiber strands and forms an inner shell surface formed to receive the structural profile; and a matrix material into which the fiber strands are respectively embedded and which is formed to be shrinkable by heating so that the fiber structure can be fastened to the structural profile with the inner shell surface by heating the matrix material. Also provided are a structural arrangement with such a reinforcing element, an aircraft or spacecraft with such a structural arrangement, as well as a method for producing such a structural arrangement.

Abstract: A reinforcing element for a structural profile, in particular for a round, oval or elliptical structural tube. The reinforcing element comprises: a fiber structure which has a hollow-cylindrical, helically wound mesh of fiber strands and forms an inner shell surface formed to receive the structural profile; and a matrix material into which the fiber strands are respectively embedded and which is formed to be shrinkable by heating so that the fiber structure can be fastened to the structural profile with the inner shell surface by heating the matrix material. Also provided are a structural arrangement with such a reinforcing element, an aircraft or spacecraft with such a structural arrangement, as well as a method for producing such a structural arrangement.

Abstract: A connecting device for manufacturing a peeling-stress-resistant connection between two components. The connecting device includes a carrier, which has a first surface and a second surface opposing the first surface. The connecting device further includes a plurality of hook and loop elements which extend both from the first and the second surface of the carrier and each have at their free ends facing away from the first or the second surface of the carrier a hook and loop head, which is arranged to enter into a hook and loop connection with a component comprising a fiber-reinforced composite material.

Abstract: A method for the manufacture of a fiber composite component reinforcement section, which bounds a cavity, whereby a supporting core, with an elastic sleeve bounding an interior space, is temporarily positioned in the cavity. The steps include: laying down fibrous material on a base molding tool to form a base element of the fiber composite component, draping fibrous material in a negative mold, arranging the supporting core on an inner surface of the fibrous material in the negative mold, positioning the negative mold fitted with the fibrous material and the supporting core, on the base element to form the reinforcement section, forming a vacuum chamber accommodating the negative mold and the base element by covering with a vacuum film, evacuating the vacuum chamber, and curing the fibrous material, whereby when using a dry fibrous material, a matrix material is injected into the fibrous material after the evacuation.

Abstract: An aircraft structural component comprising a panel element made of a fiber reinforced composite material and provided with an opening extending fully through the panel element. A reinforcing element made of a fiber reinforced composite material has an opening extending through the reinforcing element from a first surface to a second surface of the reinforcing element. The opening extending through the reinforcing element is aligned with the opening extending through the panel element. A bushing extends through the opening provided in the panel element and the opening provided in the reinforcing element and is adapted to receive an attachment device for attaching a load to the aircraft structural component. A connecting element connects the reinforcing element to the panel element in a region of the panel element adjacent to the opening extending through the panel element by means of a hook and loop connection.

Abstract: A method is provided for repairing an aircraft structural component which has a component fault in a portion adjoining a cavity of the aircraft structural component. The method includes removing a region of the aircraft structural component that has the component fault, introducing a bearing element into the cavity of the aircraft structural component through an opening, which has been formed in the aircraft structural component by the removal of the region of the aircraft structural component having the component fault, in such a way that a bearing surface of the bearing element comes to lie against a region, adjacent to the opening, of an inner surface of the aircraft structural component facing the cavity of the aircraft structural component, fixing the bearing element in its position in the cavity of the aircraft structural component, and closing the opening by means of a repair material.

Abstract: An aircraft structural component comprising a panel element made of a fiber reinforced composite material and provided with an opening extending fully through the panel element. A reinforcing element made of a fiber reinforced composite material has an opening extending through the reinforcing element from a first surface to a second surface of the reinforcing element. The opening extending through the reinforcing element is aligned with the opening extending through the panel element. A bushing extends through the opening provided in the panel element and the opening provided in the reinforcing element and is adapted to receive an attachment device for attaching a load to the aircraft structural component. A connecting element connects the reinforcing element to the panel element in a region of the panel element adjacent to the opening extending through the panel element by means of a hook and loop connection.

Abstract: An aircraft assembly is provided having a first aircraft component and a second aircraft component, at least one of the aircraft components being composed of a fibre-reinforced composite material, a connecting device connecting the first aircraft component to the second aircraft component, the connecting device including a first and a second section having a carrier element connected to the first and second aircraft components respectively, the first section having a first surface facing the first aircraft component and a second surface facing away from the first aircraft components, the second section having a first surface facing the second aircraft component and a second surface facing away from the second aircraft component. The first and second sections include a plurality of hook and loop elements extending from the second surface of the carrier element and cooperate to produce a hook and loop connection between the first and second aircraft components.

Abstract: A holding device for attaching at least one fixture to a fuselage cell structure of an aircraft, includes a basic element attached to the fuselage cell structure, to which at least one fixture element to accommodate the fixture is fastened, wherein the basic element is embodied as a hook-and-loop element, the hook-and-loop bristles of which co-act with corresponding hook-and-loop bristles of at least one fixture element, which is also embodied as a hook-and-loop element thus forming a hook-and-loop connection, wherein the space between the interengaging hook-and-loop bristles is filled with an adhesive.

Abstract: A connecting device for manufacturing a peeling-stress-resistant connection between two components. The connecting device includes a carrier, which has a first surface and a second surface opposing the first surface. The connecting device further includes a plurality of hook and loop elements which extend both from the first and the second surface of the carrier and each have at their free ends facing away from the first or the second surface of the carrier a hook and loop head, which is arranged to enter into a hook and loop connection with a component comprising a fiber-reinforced composite material.

Abstract: A method is provided for repairing an aircraft structural component which has a component fault in a portion adjoining a cavity of the aircraft structural component. The method includes removing a region of the aircraft structural component that has the component fault, introducing an expansion body into the cavity of the aircraft structural component through an opening that has been formed by the removal of the region of the aircraft structural component having the component fault, wherein the expansion body while being introduced into the cavity of the aircraft structural component is in a non-expanded state, converting the expansion body that has been introduced into the cavity of the aircraft structural component to an expanded state, and closing the opening by means of a repair material.

Abstract: A method for the manufacture of a fibre composite component reinforcement section, which bounds a cavity, whereby a supporting core, with an elastic sleeve bounding an interior space, is temporarily positioned in the cavity. The steps include: laying down fibrous material on a base moulding tool to form a base element of the fibre composite component, draping fibrous material in a negative mould, arranging the supporting core on an inner surface of the fibrous material in the negative mould, positioning the negative mould fitted with the fibrous material and the supporting core, on the base element to form the reinforcement section, forming a vacuum chamber accommodating the negative mould and the base element by covering with a vacuum film, evacuating the vacuum chamber, and curing the fibrous material, whereby when using a dry fibrous material, a matrix material is injected into the fibrous material after the evacuation.

Abstract: An aircraft assembly is provided having a first aircraft component and a second aircraft component, at least one of the aircraft components being composed of a fibre-reinforced composite material, a connecting device connecting the first aircraft component to the second aircraft component, the connecting device including a first and a second section having a carrier element connected to the first and second aircraft components respectively, the first section having a first surface facing the first aircraft component and a second surface facing away from the first aircraft components, the second section having a first surface facing the second aircraft component and a second surface facing away from the second aircraft component. The first and second sections include a plurality of hook and loop elements extending from the second surface of the carrier element and cooperate to produce a hook and loop connection between the first and second aircraft components.

Abstract: A method is provided for repairing an aircraft structural component which has a component fault in a portion adjoining a cavity of the aircraft structural component. The method includes removing a region of the aircraft structural component that has the component fault, introducing an expansion body into the cavity of the aircraft structural component through an opening that has been formed by the removal of the region of the aircraft structural component having the component fault, wherein the expansion body while being introduced into the cavity of the aircraft structural component is in a non-expanded state, converting the expansion body that has been introduced into the cavity of the aircraft structural component to an expanded state, and closing the opening by means of a repair material.

Abstract: A method is provided for repairing an aircraft structural component which has a component fault in a portion adjoining a cavity of the aircraft structural component. The method includes removing a region of the aircraft structural component that has the component fault, introducing a bearing element into the cavity of the aircraft structural component through an opening, which has been formed in the aircraft structural component by the removal of the region of the aircraft structural component having the component fault, in such a way that a bearing surface of the bearing element comes to lie against a region, adjacent to the opening, of an inner surface of the aircraft structural component facing the cavity of the aircraft structural component, fixing the bearing element in its position in the cavity of the aircraft structural component, and closing the opening by means of a repair material.