Aircraft panel structure and aircraft panel structure manufacturing method for alleviation of stress

摘要

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.

主权项

1. An aircraft panel assembly comprising:
a first aircraft panel formed of a first sheet material having a first thermal expansion coefficient, the first aircraft panel comprising a first face; a second aircraft panel formed of a second sheet material having a second thermal expansion coefficient different from the first thermal expansion coefficient, the second aircraft panel comprising a second face facing the first face, the first and second aircraft panels joined at a first discrete fastening point by at least one fastener and at a second discrete fastening point by another fastener, the first and second discrete fastening points aligned along a first notional panel join line defining the shortest distance between the fasteners along the first face, and a second notional panel join curvilinear line describing the shortest distance between the fasteners along the second face, wherein the second notional panel join curvilinear line is longer than the first notional panel join line, a stress relief feature is formed by the second notional panel join curvilinear line diverging from the first notional panel join line between the first and second discrete fastening points, and the second notional panel join curvilinear line converges to the first notional panel join line at each of the first and second discrete fastening points, and wherein said first aircraft panel comprises a structural component of an aircraft and said second aircraft panel comprises an aircraft skin or a second structural component of the aircraft.