Airbus Operations Gmbh

Daimler-benz Aerospace Airbus Gmbh

Bernd Raeckers

Wolfgang Schulze

Marc Schimmler

Thomas Kruse

Sven Werner

Lutz Wiese

A method for manufacturing a load bearing structure involves providing a panel; providing a first set of split stiffening elements on a surface of the panel, wherein the split stiffening elements of the first set have bottom surfaces and central portions with open top clearances, respectively, spaced apart from each other; providing a second set of stiffening elements having bottom surfaces and top surfaces and central portions, respectively; inserting the stiffening elements of the second set into respective open top clearances of the split stiffening elements of the first set and providing the second set of stiffening elements on the surface of the panel for forming a grate structure; and attaching top surfaces to the split stiffening elements of the first set for forming complete profiles.

Method for manufacturing a load bearing structure and such a load bearing structure

A method for testing the fracture toughness of an adhesive joint to be formed between two components made of fiber-reinforced plastic, by forming a test joint between two sample elements and applying a tensile load onto this test joint until a pre-defined value is reached. One of these sample elements is formed by one of the components of the joint to be formed, and the tensile load acts on the other sample element.

Method for testing the fracture toughness of an adhesive joint to be formed

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

The invention concerns a method for manufacturing a shell, in particular a fuselage shell, a wing shell, a horizontal stabilizer shell or a vertical stabilizer shell, that is reinforced with a plurality of stiffening elements, for forming component parts for aircraft with high dimensional stability, wherein the stiffening elements and a shell skin are made with epoxy resin from at least partially cured carbon fiber reinforced semi-finished parts, the method comprising the following steps: The invention also concerns a shell, in particular a fuselage shell, a wing shell, a horizontal stabilizer shell or a vertical stabilizer shell, manufactured in accordance with the inventive method.

Method for manufacturing a reinforced shell for forming component parts for aircraft and shell for component parts for aircraft

Fiber reinforced structural components, such as panels with honeycomb cores sandwiched between at least two outer skin layers are dried to remove moisture that may have entered into the interior of the structure. For this purpose the component is cooled in a cooling environment below the freezing point to about -5.degree. to -20.degree. C. and then exposed to a reduced pressure of less than 0.5 mbar. Under these drying conditions moisture is driven out of the component by sublimation so that the moisture does not pass through the liquid phase. The drying time may be reduced by a temperature increase to 80.degree.-100.degree. C. while maintaining the low pressure. The freezing increases the capillary action for the moisture removal. However, for an increased efficiency in the moisture removal small diameter holes, e.g. 0.1 mm bores, may be drilled into the component to facilitate the moisture escape. After drying is complete the holes are closed again e.g. by laminating further cover sheets to the component. Drying time may be reduced by a temperature increase to 80.degree.-100.degree. C. while maintaining the low pressure.

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Bremen, Germany

Bernd Raeckers