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    HIGHLY INTEGRATED INNER STRUCTURE OF A TORSION BOX OF AN AIRCRAFT LIFTING SURFACE
    4.
    发明申请
    HIGHLY INTEGRATED INNER STRUCTURE OF A TORSION BOX OF AN AIRCRAFT LIFTING SURFACE 审中-公开
    飞机提升表面扭转箱的高度集成的内部结构

    公开(公告)号：US20140048652A1

    公开(公告)日：2014-02-20

    申请号：US13964400

    申请日：2013-08-12

    申请人： AIRBUS OPERATIONS S.L.

    发明人： Francisco Javier HONORATO RUIZ ,  Francisco José CRUZ DOMINGUEZ

    IPC分类号： B64C3/28

    CPC分类号： B64C3/28 ,  B29C35/0227 ,  B29C65/02 ,  B29C66/721 ,  B29C66/7212 ,  B29C66/72141 ,  B29C66/73752 ,  B29C70/42 ,  B29L2031/3085 ,  B64C3/18 ,  B64C3/20 ,  Y02T50/43 ,  B29K2307/04

    摘要： The invention provides a method for manufacturing a monolithic torsion box inner structure (40) of an aircraft lifting surface comprising the following steps: a) providing a set of laminated preforms of a composite material for forming said torsion box inner structure (40), each laminated preform being configured for constituting a part of one component of the torsion box inner structure (40); 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 vertical direction. The invention also provides an aircraft lifting surface wherein: the inner structure (40) of each torsion box (13) is manufactured by said method and the upper and lower skins (31, 33) are attached to the torsion box inner structure (40) with mechanical attachment means.

    摘要翻译： 本发明提供一种用于制造飞行器提升表面的整体式扭转箱内部结构（40）的方法，包括以下步骤：a）提供一组用于形成所述扭转箱内部结构（40）的复合材料的层压预制件，每组 叠层预成型件构成为构成扭转箱内部结构（40）的一个部件的一部分; 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）在垂直方向脱模固化工具。 本发明还提供了一种飞机提升表面，其中：每个扭转箱（13）的内部结构（40）由所述方法制造，上部和下部表皮（31,33）附接到扭转箱内部结构（40） 具有机械附接装置。

    HORIZONTAL TAIL PLANE OF AN AIRCRAFT
    6.
    发明申请
    HORIZONTAL TAIL PLANE OF AN AIRCRAFT 审中-公开
    飞机的水平尾翼飞机

    公开(公告)号：US20150183508A1

    公开(公告)日：2015-07-02

    申请号：US14584480

    申请日：2014-12-29

    申请人： AIRBUS OPERATIONS S.L.

    发明人： Andrea Ivan MARASCO ,  Fernando PEREIRA MOSQUEIRA ,  Enrique GUINALDO FERNÁNDEZ ,  Carlos GARCÍA NIETO ,  Francisco Javier HONORATO RUIZ ,  Francisco José CRUZ DOMÍNGUEZ

    IPC分类号： B64C5/02 ,  B64C3/18

    CPC分类号： B64C5/02 ,  B64C3/18

    摘要： Horizontal tail plane of an aircraft which comprises a single torsion box which also comprises a front spar (1), a rear spar (2), an upper cover and a lower cover, ribs and two closing ribs (3), the front spar (1), the rear spar (2) and the upper and lower covers extending between said two closing ribs (3) and along the whole span of the horizontal tail plane in a symmetric layout with respect to the symmetry axis of the aircraft.

    摘要翻译： 飞机的水平尾翼平面包括一个单一的扭转箱，它还包括前翼梁（1），后翼梁（2），上盖和下盖，肋和两个关闭肋（3），前翼梁 后翼梁（2）和上盖和下盖在所述两个关闭肋（3）之间延伸并且沿着相对于飞行器的对称轴线的对称布局沿着水平尾翼平面的整个跨度延伸。

    HIGHLY INTEGRATED LEADING EDGE OF AN AIRCRAFT LIFTING SURFACE
    7.
    发明申请
    HIGHLY INTEGRATED LEADING EDGE OF AN AIRCRAFT LIFTING SURFACE 有权
    飞机提升表面的高度集成的领先优势

    公开(公告)号：US20140133987A1

    公开(公告)日：2014-05-15

    申请号：US13943115

    申请日：2013-07-16

    申请人： AIRBUS OPERATIONS S.L.

    发明人： Enrique GUINALDO FERNANDEZ ,  Francisco Javier HONORATO RUIZ ,  Francisco Jose CRUZ DOMINGUEZ

    IPC分类号： F01D5/14

    CPC分类号： F01D5/14 ,  B29D99/0028 ,  B64C3/28 ,  Y10T29/49336

    摘要： 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.

    摘要翻译： 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。

    OPTIMIZED TORSION BOX FOR AN AIRCRAFT
    9.
    发明申请
    OPTIMIZED TORSION BOX FOR AN AIRCRAFT 有权
    优化的机舱扭矩箱

    公开(公告)号：US20140138486A1

    公开(公告)日：2014-05-22

    申请号：US14085381

    申请日：2013-11-20

    申请人： AIRBUS OPERATIONS S.L.

    发明人： Enrique GUINALDO FERNADEZ ,  Francisco CRUZ DOMINGUEZ ,  Francisco Javier HONORATO RUIZ ,  Paula MÁS MÁS ,  Iker VÉLEZ DE MENDIZÁBAL ALONSO ,  Carlos GARCIA NIETO

    IPC分类号： B64C3/18

    CPC分类号： B64C3/185 ,  B64C3/18 ,  B64C3/187 ,  Y10T156/10

    摘要： The invention provides an aircraft lifting surface with a torsion box (13) of a composite material comprising an upper skin (21), a lower skin (23), a front spar (18), a rear spar (20), one or more intermediate spars (19, 19′) and a plurality of transverse ribs (25, 25′, . . . ) arranged between the rear spar (20) and its adjacent intermediate spar (19′) and/or between the front spar (18) and the adjacent intermediate spar (19) for improving its structural behavior. The invention also provides a manufacturing method of said torsion box.

    摘要翻译： 本发明提供一种具有复合材料的扭转箱（13）的飞机提升表面，该复合材料包括上皮（21），下皮（23），前翼梁（18），后翼梁（20），一个或多个 中间翼梁（19,19'）和布置在后翼梁（20）和其相邻的中间翼梁（19'）之间和/或前翼梁（18）之间的多个横向肋（25,25'...） ）和相邻的中间梁（19），用于改善其结构行为。 本发明还提供了所述扭转箱的制造方法。