Airbus Operations Gmbh

Airbus Defence and Space Gmbh

Thomas Kruse

Alois Friedberger

Wolfgang Schulze

Thomas Körwien

Andreas Helwig

Paulin Fideu

Marc Schimmler

Jens Telgkamp

Bernd Raeckers

Christopher Buchmann

Anton Maier

Jens Holtmannspötter

Thomas KÖRWIEN

Bernd Räckers

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.

Display apparatus and method for monitoring the structural integrity of a repair location

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.

Method for determining a distance between two components to be joined

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.

Component device and method for detecting damage in a bonding adhesive of the component device

A method for producing a fiber composite component assembly having at least first and second plate-shaped composite structures made from synthetic resin embedded fibers, the at least first and second fiber composite components having a plurality of partial regions not containing synthetic resin is described. The method includes positioning the at least first and second fiber composite components, the partial regions having been brought to flush conformity with each other, bonding the at least first and second positioned fiber composite components by the adhesive layer arranged in between, placing mechanical reinforcement means through the partial regions, infusing the dry partial regions with synthetic resin, and curing the synthetic resin placed in the partial regions.

Fiber composite component assembly having at least two plate-shaped composite structures and processes for preparing same

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.

Component device and method for detecting a damage in a bonding of a component device

A method for the manufacture of a fiber composite component with at least one opening, which is edged by an integral collar, a device for the execution of a method of this type with a mold core, which has at least one convexity for the formation of a component section in the form of a bulge, also a fiber composite component with a multiplicity of openings, each of which is edged by an integral collar.

Method and a device for the manufacture of a fibre composite component, and a fibre composite component

Method for connecting two intermediate products for forming a fiber composite product, wherein the two intermediate products respectively are composite fiber material with a layer of matrix material and reinforcing fibers extending therein by connecting areas that adjoin one another in an overlapping region of the interconnected intermediate products, with the method including applying an adhesive layer with an adhesive film with connecting particles onto the connecting areas of the intermediate products, arranging the second intermediate product on the first intermediate product or vice versa so the connecting areas at least partially overlap one another, and connecting the two intermediate products. A structural component is also disclosed with at least a first and a second fiber-reinforced intermediate product.

Method for connecting fiber-reinforced intermediate products for producing a structural fiber composite product, such a structural fiber composite product and a method and device for producing an adhesive layer

A structural component includes a fiber composite material structure having an outer surface and an electrically conductive metal profile disposed on the outer surface of the fiber composite material structure. The metal profile provides provide improved electrical conductivity of the structural component and component protection.

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Hermannsburg, Germany

Thomas Kruse