The invention provides an integrated aircraft structure (10), such as a fuselage, with reinforcing elements (51, 53) in areas of the structure that need them because they have openings or are subjected to high loads. The structure (10) comprises a skin (13), a plurality of stringers (15) and a plurality of frames (17) with mouseholes for the passage of stringers (15) at their crossing zones. The reinforcing elements (51, 53) are configured with a suitable shape to be superimposed to the stringers (15) in said areas. The invention also provides manufacturing processes of said integrated aircraft structure (10).
Aircraft structure with integrated reinforcing elements
Flugzeugstruktur mit integrierten Verstärkungselementen
Structure d'aéronef avec éléments de renfort intégrés
2015-12-23
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
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