| 摘要 |
<p>The aim of the invention is to reduce the multiple costs of manufacture, assembly, use, and upkeep connected with the assembly of window coaming on aircraft fuselages. To this end, the invention provides a particular shape for the coaming (20) connected to the fuselage skin (30) according to a specific assembly method. Said shape enables, inter alia, the window coaming to be fitted onto the skin by means of adhesion and also coaming to be dispensed with between the fuselage and the window. In one embodiment, composite material window coaming (20) has a wall totally in the shape of a crown (21) that is connected, through co-adhesion, to the inner surface of the fuselage skin (30), also made of composite material. The skin (30) is cut into a window-receiving opening (40), and the coaming (20) has a T-shaped cross-section, wherein the bar of the "T" that forms the crown (21) includes two portions (21a) and (21b) having substantially equal lengths "I".</p> |
