Abstract: A composite component system includes a base component with a first component fiber ply and a second component fiber ply and a repair insert with a first repair fiber ply and a second repair fiber ply. The base component is connected to the repair insert by an adhesive joint. The first component fiber ply has an interface surface connected to the interface surface of the first repair fiber ply by the adhesive joint. The second component fiber ply has an interface surface connected to the interface surface of the second repair fiber ply by the adhesive joint. The first component fiber ply has a fiber orientation corresponding substantially to a fiber orientation of the first repair fiber ply. The interface surface of the first repair fiber ply completely overlaps the interface surface of the first component fiber ply.

Abstract: The invention relates to a method for repairing a damaged point of a fiber composite component which is formed from at least one fiber ply of a fiber material of a fiber composite substance and a matrix material of the fiber composite substance, in which matrix material the fiber material is embedded, wherein the method comprises the following steps: removing the damaged point from the fiber composite component and producing a repair cavity in the fiber composite component, introducing at least one reparative fiber ply of a fiber material into the repair cavity produced in the fiber composite component, and curing the matrix material, in which the fiber material of the reparative fiber ply is embedded, after introducing the reparative fiber ply into the repair cavity of the fiber composite component, wherein at least one reparative fiber ply having a ply thickness that is smaller than the ply thickness of the fiber plies of the rest of the fiber composite component is introduced into the repair cavity.

Abstract: A method for determining a distance between components has the steps of providing a first conductive section in or on the first component in a region directed toward the second component, providing a second conductive section in or on the second component in a region directed toward the first conductive section, feeding a first voltage pulse into a first connection of the first conductive section, capturing a reflection voltage pulse in response to the first voltage pulse at the first connection, determining an impedance profile along the first conductive section by evaluating the reflection voltage pulse, and determining a distance between the components along the first conductive section by calculating a corresponding local distance, associated with the determined impedance profile, between the first conductive section and the second conductive section.

Abstract: A composite component system includes a base component with a first component fiber ply and a second component fiber ply and a repair insert with a first repair fiber ply and a second repair fiber ply. The base component is connected to the repair insert by an adhesive joint. The first component fiber ply has an interface surface connected to the interface surface of the first repair fiber ply by the adhesive joint. The second component fiber ply has an interface surface connected to the interface surface of the second repair fiber ply by the adhesive joint. The first component fiber ply has a fiber orientation corresponding substantially to a fiber orientation of the first repair fiber ply. The interface surface of the first repair fiber ply completely overlaps the interface surface of the first component fiber ply.

Abstract: An indication device for monitoring the structural integrity of a repair location on a laminate structure, produced from a composite material, of a part of an aircraft outer skin is specified. The indication device has at least one elongate, thin indicator strip. The indicator strip is detachably applied to the outer layer of the laminate structure in the immediate vicinity of the repair location. The indicator strip is designed to indicate a predefined residual strength of an adhesive joint of a repair patch to the surrounding composite material.

Abstract: A method for categorizing a fracture surface of a component. A digital image of the fracture surface is generated. The digital image or one or more segments of the digital image is/are analyzed, wherein a category of a fracture pattern is assigned to one or more regions of the digital image or of one or more segments based on detection and statistical evaluation of spatial distribution of the smallest homogeneous image units (pixels) or image elements, and, provided that multiple regions and/or multiple segments of the digital image were analyzed, information about the regions and/or details of the digital image and categories of fracture patterns determined and assigned to them are linked to each other, and a category is assigned to the fracture surface based on this link. The method permits automatic, self-learning-categorization of fracture surfaces, for example for series tests carried out for joining technologies.

Abstract: The disclosure relates to a component device, in particular for a primary supporting component of an aircraft, which comprises a first component element, a second component element, a bonding providing a connection between the first component element and the second component element, a marker substance device configured to dispense a volatile marker gas to the environment when in contact with the surrounding air and being hermetically sealed from the surrounding air by the first component element, the second component element, and/or the bonding if the bonding is not damaged, and a detector device configured to detect the marker gas dispensed by the marker substance device.

Abstract: The disclosure relates to a component device, in particular for a primary supporting component of an aircraft, the component device having a first component element, a second component element, a bonding providing a connection between the first component element and the second component element, and a detector device having at least one interior space sensor device configured to measure a change in a pressure and/or a concentration of a gas surrounding the interior space sensor device. The first component element, the second component element, and the bonding confine an interior space. The interior space sensor device is arranged in the interior space.

Abstract: A method for categorizing a fracture surface of a component. A digital image of the fracture surface is generated. The digital image or one or more segments of the digital image is/are analyzed, wherein a category of a fracture pattern is assigned to one or more regions of the digital image or of one or more segments based on detection and statistical evaluation of spatial distribution of the smallest homogeneous image units (pixels) or image elements, and, provided that multiple regions and/or multiple segments of the digital image were analyzed, information about the regions and/or details of the digital image and categories of fracture patterns determined and assigned to them are linked to each other, and a category is assigned to the fracture surface based on this link. The method permits automatic, self-learning-categorization of fracture surfaces, for example for series tests carried out for joining technologies.

Abstract: A coated composite component includes, in this order, a composite component, a fluorine-containing film and/or a fluorine-containing woven fabric, knitted fabric or crocheted fabric, and a tear-off fabric. A method for producing a coated composite component including, in this order, a composite component, a fluorine-containing film and/or a fluorine-containing woven fabric, knitted fabric or crocheted fabric, and a tear-off fabric.

Abstract: A method for joining structural elements to a component made of at least one fiber-reinforced plastics material, includes providing at least two structural elements made of at least one fiber-reinforced plastics material having a particular matrix; providing at least one film element made of a thermoplastic heavy-duty material; arranging the at least one film element on a surface of one of the structural elements or between surfaces to be joined of the at least two structural elements to be joined; and producing the component to be joined in a curing process.

Abstract: A method for providing spacers on a construction component to be adhered involves applying a planar formation, including passages, on the construction component to be adhered, and inserting a setting liquid in the passages of the planar formation, so that the liquid forms spacer on the construction component to be adhered after setting and peeling off the planar formation. The spacer ensures a predetermined minimum bondline when adhering the construction component.

Abstract: A method for determining a distance between a first component (2) and a second component (4) has the steps of providing at least one first conductive section (8) in or on the first component (2) in a region directed toward the second component (4), providing at least one second conductive section (12) in or on the second component (4) in a region directed toward the first conductive section, feeding a first voltage pulse into a first connection of the first conductive section, capturing a reflection voltage pulse in response to the first voltage pulse at the first connection, determining an impedance profile along the at least one first conductive section by evaluating the reflection voltage pulse, and determining at least one distance between the first component (2) and the second component (4) along the at least one first conductive section by calculating at least one corresponding local distance, associated with the determined impedance profile, between the at least one first conductive section (8) and the

Abstract: A structural element includes a first component and a second component; a bonded joint, by which the first component and the second component are interconnected; and an indication bolt, which is fixed to the first component and the second component. The indication bolt is designed to indicate when the first component and the second component have moved relative one another.

Abstract: A method for joining structural elements to a component made of at least one fiber-reinforced plastics material, includes providing at least two structural elements made of at least one fiber-reinforced plastics material having a particular matrix; providing at least one film element made of a thermoplastic heavy-duty material; arranging the at least one film element on a surface of one of the structural elements or between surfaces to be joined of the at least two structural elements to be joined; and producing the component to be joined in a curing process.

Abstract: The disclosure relates to a component device, in particular for a primary supporting component of an aircraft, the component device having a first component element, a second component element, a bonding providing a connection between the first component element and the second component element, and a detector device having at least one interior space sensor device configured to measure a change in a pressure and/or a concentration of a gas surrounding the interior space sensor device. The first component element, the second component element, and the bonding confine an interior space. The interior space sensor device is arranged in the interior space.

Abstract: The disclosure relates to a component device, in particular for a primary supporting component of an aircraft, which comprises a first component element, a second component element, a bonding providing a connection between the first component element and the second component element, a marker substance device configured to dispense a volatile marker gas to the environment when in contact with the surrounding air and being hermetically sealed from the surrounding air by the first component element, the second component element, and/or the bonding if the bonding is not damaged, and a detector device configured to detect the marker gas dispensed by the marker substance device.

Abstract: A coated composite component includes, in this order, a composite component, a fluorine-containing film and/or a fluorine-containing woven fabric, knitted fabric or crocheted fabric, and a tear-off fabric. A method for producing a coated composite component including, in this order, a composite component, a fluorine-containing film and/or a fluorine-containing woven fabric, knitted fabric or crocheted fabric, and a tear-off fabric.

Abstract: A method is provided for manufacturing a radome. The method has the following steps: creation of a contoured fit of at least one section of an inner surface of a wall of the radome; arrangement of a plurality of planar photosensitive semiconductor elements on an outer surface of the contoured fit; placement of the contoured fit with the plurality of planar photosensitive semiconductor elements on the at least one section of the inner surface of the wall; establishing of a connection between the plurality of planar photosensitive semiconductor elements and the wall; and removal of the contoured fit from the radome. This method enables the simple manufacture of a radome with a layer having several semiconductor elements for the electromagnetic shielding of the interior of the radome.

Abstract: A method is provided for manufacturing a radome. The method has the following steps: creation of a contoured fit of at least one section of an inner surface of a wall of the radome; arrangement of a plurality of planar photosensitive semiconductor elements on an outer surface of the contoured fit; placement of the contoured fit with the plurality of planar photosensitive semiconductor elements on the at least one section of the inner surface of the wall; establishing of a connection between the plurality of planar photosensitive semiconductor elements and the wall; and removal of the contoured fit from the radome. This method enables the simple manufacture of a radome with a layer having several semiconductor elements for the electromagnetic shielding of the interior of the radome.