Corrosion-resistant connection between a first component and a second component
A technology of components and contact areas, applied in transportation and packaging, thin material handling, fuselage bulkheads, etc., can solve problems such as different and complex thermal expansion coefficients
Active Publication Date: 2014-03-19
AIRBUS OPERATIONS GMBH
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Problems solved by technology
Mechanically joining carbon fiber reinforced components to conventional components such as those formed from aluminum alloy materials to form complex joining arrangements is problematic for a number of reasons
[0003] On the one hand, the aforementioned materials have different coefficients of thermal expansion, which can lead to temperature-induced stresses in this connection
Method used
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Embodiment Construction
[0013] In the drawings, the same structural elements have the same reference numerals.
[0014] figure 1 Is a perspective view of a detail of an aircraft fuselage employing a connection 1 formed according to the invention.
[0015] To the fuselage skin 2 of the fuselage a number of reinforcement profiles (called "stringers") are fastened, of which only reinforcement profiles 3 to 5 are shown for the sake of clarity of the drawing. The reinforcement profiles 3 to 5 , each having a T-shaped cross-section, extend parallel to the longitudinal axis of the fuselage (not shown) at substantially the same distance. A large number of ribs extend transversely relative to said reinforcement profiles 3 to 5, at figure 1 Only one of the ribs 6 is marked in the representation of . The rib 6 is preferably an annular rib formed of high-strength aluminum alloy material.
[0016] The ribs 6 (first part) are mechanically connected to the fuselage skin 2 by means of curved angle brackets 7 (se...
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Abstract
The invention relates to a connection 1 between a first component and a second component, the first component being formed from an aluminium alloy in particular and the second component being formed from a carbon-fibre-reinforced plastics material in particular. The first component is a rib 6 in particular and the second component is preferably an angle bracket 7, with which the rib 6 is connected to an aircraft fuselage skin 2 within a fuselage reinforcement structure. The connection 1 between the components comprises, according to the invention, a ceramic coating 16 which is applied for protection against corrosion at least in the region of a contact area 9 between the components, the components being riveted and / or adhesively bonded. The ceramic coating 16 is less than 0.1 mm thick and may be formed from a mixture of aluminium oxide (Al2O3) and TiO2 for example.
Description
technical field [0001] The invention relates to a connection between a first part formed of metallic material, in particular an aluminum alloy, and a second part made of composite The material is formed, in particular from a carbon fiber reinforced plastic material. Background technique [0002] Components made of carbon fiber reinforced plastic materials are increasingly being used in the modern aircraft construction industry as connection fittings for reinforcing the fuselage. Mechanically joining carbon fiber reinforced components to conventional components, eg formed of aluminum alloy materials, to form complex joining arrangements has been problematic for a number of reasons. [0003] On the one hand, the aforementioned materials have different coefficients of thermal expansion, which can lead to temperature-induced stresses in the connection. On the other hand, the mechanical connection between the metal part and the composite fiber part is largely susceptible to cor...
Claims
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IPC IPC(8): B64C1/12
CPCB64C1/12Y10T428/263
Inventor 托尔斯腾·雷敏豪克·克斯汀托尔斯腾·施罗尔
Owner AIRBUS OPERATIONS GMBH