Airbus Operations Gmbh

Raymond Bullock

Antony Charles Peacock

Christopher Payne

Peter Griggs

Glenn Watson

Thomas Burvill

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

An aircraft wing cover () comprising an integrally stiffened sandwich panel including first and second skins () sandwiching a core layer (), wherein at least one of the skins has a plurality of spanwise extending integral regions of increased thickness () accommodated by corresponding regions () of decreased thickness in the core. Also, a method of fabricating an aircraft wing cover, and a method of designing an aircraft wing.

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Bristol, United Kingdom

Raymond Bullock