An aircraft panel assembly comprising a first panel constructed from a first sheet material having a first thermal expansion coefficient, the first panel comprising a first face, a second panel constructed from a second sheet material having a second thermal expansion coefficient different from the first thermal expansion coefficient, the second panel comprising a second face facing the first face, the first and second panels being joined at a first discrete fastening point and a second discrete fastening point, the fastening points being connected by a first notional panel join line describing the shortest distance between the fasteners along the first face, and a second notional panel join line describing the shortest distance between the fasteners along the second face, in which the first panel comprises a stress relief feature between the fastening points such that the first notional panel join line diverges from, and converges with, the second notional panel join line.
Aircraft panel structure and aircraft panel structure manufacturing method for alleviation of stress
29.09.2015
Patent
Elektronische Ressource
Englisch
IPC: | B32B LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM , Schichtkörper, d.h. aus Ebenen oder gewölbten Schichten, z.B. mit zell- oder wabenförmiger Form, aufgebaute Erzeugnisse / B23P Sonstige Metallbearbeitung , OTHER WORKING OF METAL / B64C AEROPLANES , Flugzeuge |
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