A method for manufacturing a leading edge (11) profile section (30) of an aircraft lifting surface is provided. The method comprises the following steps: a) providing a set of laminated preforms (31,33) of a composite material configured with a suitable shape for constituting the leading edge profile section; b) arranging said laminated preforms in a curing tooling and subjecting the assembly to an autoclave cycle to co-cure said laminated preforms; c) demoulding the curing tooling in a spanwise direction towards the aircraft symmetry plane. The invention also comprises a leading edge profile section (30) manufactured by said method comprising in addition to the skin of the leading edge profile section, one or more of the following structural elements: an auxiliary spar (33), a longitudinal stiffener (35) reinforcing an auxiliary spar, a longitudinal stringer (37,37') reinforcing the skin of the leading edge profile.
Highly integrated leading edge of an aircraft lifting surface
Hochintegrierte Eintrittskante einer Flugzeugtragfläche
Bord d'attaque hautement intégré d'une surface de portance d'un aéronef
2016-08-31
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
Highly integrated leading edge of an aircraft lifting surface
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