Airbus Defence and Space Gmbh

Airbus (sas)

Airbus Operations Gmbh

Airbus Helicopters Deutschland Gmbh

Thomas Meer

Alois Friedberger

Tamas Havar

Andreas Helwig

Matthias Geistbeck

Christian Metzner

Georg Wachinger

Uwe Beier

Sebastian Heckner

Meinhard Meyer

Thomas Koerwien

Patricia Parlevliet

Jonas Gruenewald

Thomas Körwien

Christian Lammel

Sabine Metzech

Robert Meissner

Oliver Rohr

Jens Holtmannspoetter

Jens Holtmannspötter

Andreas Roessmann

Helmut Wehlan

Michael Hoffmann

Johann Göbel

Jonas GRÜNEWALD

Johann GÖBEL

Peter Scheid

Andreas Geßler

Christian Thum

Andreas Rössmann

Robert Meißner

Mathias Geistbeck

A joining method and assembly for an aircraft. To improve the characteristics or permit hitherto impossible connections between thermoplastic and thermoset components, a multi-material joining method is disclosed in which a thermoplastic connecting region is formed on the thermoplastic component. The connecting region is connected to the thermoset component by interdiffusion. For this purpose, the uncured second component is brought into contact with the connecting region and heat is supplied. An interdiffusion layer is formed which fixedly connects the second component and the connecting region to one another and thus joins the first component to the second component.

Joining method and assembly for an aircraft

A method for detecting surface impurities on a surface of a component by X-ray fluorescence analysis uses a hand spectroscope for application to the surface of a component. The hand spectroscope comprises an X-ray source, a fluorescent radiation detector, an analyzer and a display. The method comprises irradiating the surface of the component with X-rays using the X-ray source; detecting fluorescent radiation, which is emitted by the surface of the component as a result of the irradiation with the X-rays, using the fluorescent radiation detector; measuring a radiation spectrum of the detected fluorescent radiation; generating an evaluation result by analyzing the measured radiation spectrum using the analyzer, the evaluation result comprising a quantitative measure of the surface impurity of the surface due to predetermined characteristic substances; and outputting the generated evaluation result on the display.

Method for detecting surface impurities by X-ray fluorescence analysis

A sandwich component has a first cover layer, a second cover layer, and a core disposed therebetween. In the sandwich component, the cover layers are each formed from an outer layer made of a fiber-reinforced thermoplast material having greater resistance to a certain solvent and, fused therewith, an inner layer made of a thermoplast material having lower resistance to the solvent. The core has outer layers, each of which is formed from a thermoplast material having lower resistance to the solvent, and an inner structure, which is formed entirely or partially from a thermoplast material having greater resistance to the solvent. The inner layers of the cover layers were each fused with one of the outer layers of the core with the use of the solvent.

Sandwich component and method for producing a sandwich component

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.

Coated composite component

A connection element includes a composite component with a cured epoxy resin, a first layer including a first thermoplastic polymer and an intermediate layer arranged between the composite component and the first layer, the first layer containing both the cured epoxy resin of the composite component and the first thermoplastic polymer of the first layer. The first thermoplastic polymer has a melting point above a curing temperature of the epoxy resin and is soluble at a temperature of at least 150&#xb0; C. in the epoxy resin used for producing the composite component.

Connection element, connection arrangement, method for producing a connection element and method for producing a connection arrangement

A fiber composite component includes a composite including cured matrix material and a fiber material embedded therein. At least one partial area of the fiber composite component is provided with at least one thread, which undulates as it extends along a surface area of the composite, so that sections of the thread alternately run inside of the composite and outside of the composite. An adhesive arrangement for such fiber composite components is also disclosed. Finally, methods for manufacturing such a fiber composite component or for manufacturing such an adhesive arrangement are disclosed.

Method for manufacturing a fiber composite component

The invention relates to a connection arrangement for connecting two profiled elements in a seamless and aerodynamically smooth manner in order to form a profiled surface around which a laminar flow is possible. A first profiled element has a first fixing strip that extends towards the second profiled element, and the surface of the first fixing strip is lower than the surfaces of the profiled elements in the outward direction. Furthermore, the second profiled element has a second fixing strip which is molded on the inside and which is arranged below the first fixing strip, and the two profiled elements are rigidly connected to each other by means of the second fixing strip. A filler region that can be found below the connecting surface between the profiled surfaces and above the fixing strip surface is tilled with at least two layers of cured filling material. A method for filling the filling region with filling material and a device for carrying out the method are also claimed.

Connection arrangement for connecting two profiled elements in an aerodynamically smooth manner, method for producing said connection arrangement, and device for carrying out the method

The invention concerns a method of connecting a first material to a second material by means of a heat-activatable adhesive material () in aircraft construction, wherein the adhesive material () is arranged between the first material and the second material and an induction heat which is adequate to activate the adhesive material () is generated. The first material and/or the second material and/or the adhesive material () have an induction heat-generating means. The induction heat-generating means is a non-woven metallic mesh and/or the induction heat-generating means () has an amount of carbon fibers for induction heat generation. The invention further concerns an apparatus comprising a first material and a second material, wherein the first material and the second material have a connection which can be produced by a heat-activatable adhesive material arranged between the first material and the second material, in accordance with the method in accordance with the invention.

Method for connecting a first material to a second material in aircraft construction

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Egmating, Germany

Thomas Meer