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    • 7. 发明申请
    • HIGHLY INTEGRATED LEADING EDGE OF AN AIRCRAFT LIFTING SURFACE
    • 飞机提升表面的高度集成的领先优势
    • US20140133987A1
    • 2014-05-15
    • US13943115
    • 2013-07-16
    • AIRBUS OPERATIONS S.L.
    • Enrique GUINALDO FERNANDEZFrancisco Javier HONORATO RUIZFrancisco Jose CRUZ DOMINGUEZ
    • F01D5/14
    • F01D5/14B29D99/0028B64C3/28Y10T29/49336
    • A method for manufacturing a leading edge profile section of an aircraft lifting surface is provided. The method comprises the following steps: a) providing a set of laminated preforms 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 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, a longitudinal stiffener reinforcing an auxiliary spar, a longitudinal stringer reinforcing the skin of the leading edge profile.
    • 提供一种用于制造飞行器提升表面的前缘轮廓部分的方法。 该方法包括以下步骤:a)提供一组复合材料的叠层预成型件,该复合材料被构造成用于构成前缘型材部分的合适形状; b)将所述层压预制件布置在固化工具中,并使组件经受高压釜循环以共同固化所述层压预制件; c)沿翼展方向将飞机对称平面上的固化工具脱模。 本发明还包括通过所述方法制造的前缘轮廓部分,除了前缘轮廓部分的皮肤之外,还包括一个或多个以下结构元件:辅助翼梁,加强辅助翼梁的纵向加强筋,纵向纵梁 加强前缘轮廓的皮肤。