CN101678890B - 成形的复合长桁及其制造方法 - Google Patents

成形的复合长桁及其制造方法 Download PDF

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CN101678890B
CN101678890B CN2008800165238A CN200880016523A CN101678890B CN 101678890 B CN101678890 B CN 101678890B CN 2008800165238 A CN2008800165238 A CN 2008800165238A CN 200880016523 A CN200880016523 A CN 200880016523A CN 101678890 B CN101678890 B CN 101678890B
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CN101678890A (zh
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J·C·古兹曼
D·A·麦克卡威尔
D·M·罗特
B·G·罗宾斯
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
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    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
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    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C43/00—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor
    • B29C43/02—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor of articles of definite length, i.e. discrete articles
    • B29C43/10—Isostatic pressing, i.e. using non-rigid pressure-exerting members against rigid parts or dies
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
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    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
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    • B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
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    • B29C70/342—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using isostatic pressure
    • B—PERFORMING OPERATIONS; TRANSPORTING
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    • B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
    • B29D99/00—Subject matter not provided for in other groups of this subclass
    • B29D99/001—Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings
    • B29D99/0014—Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings provided with ridges or ribs, e.g. joined ribs
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/18—Spars; Ribs; Stringers
    • B64C3/182—Stringers, longerons
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
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    • B29C2043/3649—Inflatable bladders using gas or fluid and related details
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C2001/0054—Fuselage structures substantially made from particular materials
    • B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials
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    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
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    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
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    • Y10T156/00—Adhesive bonding and miscellaneous chemical manufacture
    • Y10T156/10—Methods of surface bonding and/or assembly therefor
    • Y10T156/1002—Methods of surface bonding and/or assembly therefor with permanent bending or reshaping or surface deformation of self sustaining lamina
    • Y10T156/1028—Methods of surface bonding and/or assembly therefor with permanent bending or reshaping or surface deformation of self sustaining lamina by bending, drawing or stretch forming sheet to assume shape of configured lamina while in contact therewith
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
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    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/31504—Composite [nonstructural laminate]

Abstract

一个飞行器的加强蒙皮壁板(150)包括一个飞行器的复合材料蒙皮壁板及一个与飞行器蒙皮壁板固结的复合长桁。该长桁有一对长桁侧面(304)，各自从长桁顶部(302)延伸至腿部(308)。长桁侧面各自穿过一个宽半径的光滑连续曲线延伸到长桁腿部。该宽半径的光滑连续曲线可在长桁侧面向长桁腿部过渡的区域内邻近长桁侧面底部。

Description

成形的复合长桁及其制造方法
技术领域
此处描述的实施例一般涉及飞行器长桁，且更加具体地，涉及成形的复合长桁及其制造方法。
背景技术
飞行器一般包括一个机身，其可被当作基本骨架，蒙皮壁板与机身连接来形成一个光滑的空气动力学外表面。机翼也包括覆盖着蒙皮壁板的基本结构。通常情况下，蒙皮壁板轻且薄来使飞行器的重量最小化以及增加其有效载荷及航程。因为蒙皮壁板较薄，所以它们通常是柔性的且需要固定以防止在飞行中发生不希望有的运动、挠曲及振动。
帽形长桁在商用及军用飞行器上用以固定金属机身部件及金属机翼蒙皮已在航空工业中使用了数十年。这些长桁由带有锐角的薄金属壁板组成来形成梯形形状。相对简单的金属成形技术用来将金属弯曲成该形状所要求的锐角。这些金属成形技术包括弯曲成形或将金属卷成帽形长桁形状。这些技术可使生产的帽形长桁具有急转(tight)的、恒角弯曲的及直的或平坦的腿部。比如在图1中，一个帽形长桁10通过一系列附着在沿着帽形长桁10腿部16间隙处的紧固件25(在图中标出两个)附在机身蒙皮壁板20上。该帽形长桁10为具有一个平坦的上表面12及与腿部16呈一定角度的斜侧面14的梯形，其中腿部16与平坦的上表面12大致对齐。侧面14及腿部16之间交叉处的特征为陡的、急转的或具有一个小的曲率半径。
包括树脂基体及填充物的复合材料因其相对轻的重量及良好的物理性能在航空工业中得到了越来越多的应用。一般来说，填充物在性质上可以是增强的或非增强的，也可以是多种形态，比如粉末、微粒、单向纤维的纤维带材、织物等等。树脂为包括比如通常使用的环氧树脂的有机聚合物材料。
随着复合材料(比如碳纤维及环氧基树脂)在机身蒙皮及机翼蒙皮壁板工业中更加普遍，帽形长桁由于种种原因仍受欢迎。比如，帽形长桁可通过单堆叠的材料来制造，而其它较不常见的形状比如I型、J型或T型紧固件要求多堆叠及半径填充物的组合来制造。
随着长桁由金属材料向复合材料的转变，长桁的形状也发生了改变，直腿及急弯的帽形长桁不再是首选。这主要是由于传统的帽形结构的性能已被很好的了解，而且当制造用于在其中固化复合帽的工具时，有着相对较小半径细节的直或平的形状更易于制造。
复合帽形长桁现已广泛应用于一定的商用运输飞行器。将复合长桁附着于机身部分工序的一个例子如图2所示。一个帽形长桁10靠在机身背靠半刚性垫板35的蒙皮上。中空的帽形长桁10内部有一个可充气的橡胶囊36，帽形长桁10的外部覆盖着内模线(IML)工具。当内模线(IML)工具在帽形长桁10上提供外部压力时橡胶囊36膨胀。因此，帽形长桁10通过内模线工具30(及橡胶囊36)的压力及树脂的固化固结于机身蒙皮20，而垫板35控制着机身蒙皮20的轮廓。
该内模线制造方法要求若干个无缺陷的动作。比如，复合材料必须精确地放置在内模线模具型腔内以避免过填充或填充不足空隙。橡胶囊必须在固化过程中膨胀来施加压缩及固化压力。垫板必须有足够的柔性来允许材料厚度上的变化及/或层的错位，同时需要有足够的刚度来产生一个光滑的空气动力学表面。
一个OML(外模线)固化过程如图3所示。这些形状上与帽形长桁10相似的垫板42，辅助在固化循环中将复合材料压入半径内，同时辅助消除不规则。因此，机身蒙皮20依靠在外模线工具(OML)32上，且帽形长桁10靠在机身20上，该帽形长桁10内部有一个囊36。符合帽形长桁10外部形状的垫板42靠在长桁10上。袋40至少可封住垫板42及机身蒙皮20的上表面。对袋40抽真空的同时囊36膨胀且通过内模线工具32在树脂固化的过程中施加压力将帽形长桁10固结在机身上以使复合机身蒙皮接合到复合长桁10上。这种辅助垫板壁板共同固化的方法要求制造与使用数百个独特设计的高维护的垫板及相关的标准工具，这会显著增加费用负担。
因此，希望能发展复合长桁及其制造方法来简化工艺过程及降低费用。除此外，希望复合长桁有大的半径以帮助复合板坯成形为长桁。更进一步地，当用复合材料制造时，长桁的形状在结构上(即抗柱屈曲(resist column buckling)及四点弯曲)应表现得能够与传统的梯形帽相同或优于传统梯形帽。除此外，还有对于将复合长桁制造成在靠近长桁底部时具有光滑及平缓(较大)的曲率半径并且消除使用垫板辅助共同固化长桁与壁板的制造方法的需求。此外，对于复合长桁的其它所希望具有的特征及特点将在以下的详细说明及附加权利要求连同附图及前面的技术领域及背景中表明。
发明内容
一个示例性的实施例提供了飞行器的加强蒙皮壁板，该加强蒙皮壁板包括复合材料的飞行器蒙皮壁板及与该飞行器蒙皮壁板固结的复合长桁。该长桁具有一对各自从长桁顶部延伸至长桁腿部的长桁侧面。该长桁侧面各自平滑并连续地弯曲穿过一个宽半径曲线到长桁腿部。
另一个示例性的实施例提供了一个复合材料的加强壁板及一个与该壁板固结的复合长桁。该长桁具有一对长桁侧面，每个长桁侧面从长桁顶部延伸至长桁腿部。一个附着区域包括一部分长桁及邻近附着在壁板上长桁点的一部分壁板。该附着区域基本上不损坏接分离长桁复合材料的填充物。
一个实施例的更进一步的例子提供了一种用长桁加强壁板的方法。该方法包括确定待加强的复合壁板上的长桁的位置及间距和将复合壁板定位在模具上的步骤。其还进一步包括在确定的位置及间距处将符合要被形成的长桁的形状的结构(form)放置在复合壁板上。进一步地，该方法还包括准备叠层(lay up)的复合材料以形成长桁，将准备好的叠层的复合材料放置在各结构上；以及至少将复合壁板及叠层覆盖的结构封入一个真空袋内。该长桁在热及压力下固结在复合壁板上来制造加强的复合壁板。所制造的该复合壁板特点是每个长桁包括一对穿过一个宽半径的连续曲线平滑延伸到长桁腿部的长桁侧面。
附图说明
不同的实施例将在下文中结合以下的图进行描述，这些图实际上是示意图，并不是按比例缩放，其中相同的数字代表相同的单位，而且
图1为一个附着于飞行器蒙皮壁板的现有技术的帽形长桁的透视图；
图2为使用膨胀的囊及垫板的内模线叠层的现有技术的示意性端视图。
图3为使用垫板及内置囊的外模线叠层的现有技术的示意性端视图；
图4为使用外模线工具来制造成形的复合长桁的叠层的示例性实施例的示意性端视图；
图5-9示出了复合长桁形状端视图的示例性实施例的非限制的列举；而且
图10示出了一种制造加强壁板方法的示例性实施例。
具体实施方式
以下详细描述实际上只是示范性的，在应用及使用时并不限制于所描述的实施例。此外，并无意限定在前述的技术领域、背景、概要或以下的详细描述内。
示例性的实施例提供了改进的长桁结构及与待加强的壁板的固结。通过重新构造长桁的形状来消除急转半径，实施例提供了一个大曲率半径的光滑形状，至少在此长桁侧面合并入长桁腿部。长桁侧面可具有一个拐点即一个平滑的转变点。用来形成长桁的复合材料被自然地制成褶皱状以符合光滑形状。造型足够光滑及平缓(即没有急剧的转变及急转半径)以使其可允许使用带层来替代织物，这样可以显著减轻重量。在不损害长桁性能的情况下保持了结构的完整性。
总得来说，带有侧面的长桁的一些示例性实施例包括一个过渡区，该过渡区相应的包括一个拐点，在拐点处长桁侧面的曲率由凸曲线光滑过渡为凹曲线或从凹过渡为凸曲线。术语“光滑”涉及长桁的曲率，意为在曲线的切点由直线向曲线过渡或在两条曲线相切处由一条曲线向另一条曲线过渡。术语“连续的”是关于曲线，意为在光滑的曲率上没有不连续或急剧的弯曲或扭折。过渡区可位于沿着长桁侧面邻近长桁中心(相对长桁高度)或邻近长桁侧面的较低端部或较高端部。长桁的示例性实施例在垂直中心线的任一侧均是对称的，如图5-9所示，比如如下所述。
示例性的实施例允许将织物基于其自身内在的柔性通过其自然的路径制成褶皱状。这可简化制造工艺。带或织物应用于成形的固化芯轴上，不需要长桁预成形操作，而这对于传统的梯形帽形长桁中的急转半径是需要的。这些特殊形状的长桁所用的固化芯轴可以是从多种材料中选出来的，包括比如轻薄(flyaway)材料(即低密度的泡沫，其可消除使用膨胀囊的必要性)、膨胀的橡胶囊或一个可移动的实心或中空芯轴。可基于具体的运转性能比如声衰减、阻燃及结构承载能力来选择泡沫芯轴。通过独特的形状提高长桁的结构承载能力，可实现横截面的减小及重量的减轻。
图4为叠层100的示例性实施例，其包括一个支撑飞行器蒙皮壁板150比如机身或机翼壁板下侧的外模线工具200。一个芯轴或膨胀的囊120位于飞行器蒙皮壁板150的上表面，柔性的复合层110在芯轴或膨胀的囊上被制成褶皱状。一个真空袋130密封至少褶皱层芯轴或囊120，以便在袋130抽真空时施加压力将层110压在芯轴或囊120上。因为层110褶皱而形成的渐进光滑曲线，示例性实施例没有尖锐或急转角，且具有在层110固化时沿待形成的长桁的侧面的拐点102。当层110在压力及层110与蒙皮壁板150联合固化的作用下固结于飞行器蒙皮壁板150时，从层110形成的长桁300(图6)光滑弯曲且长桁腿部308从长桁300的侧面304以没有任何急转弯、“扭折”或急转角的光滑曲线方式而延伸。长桁300可被称为抛物线形或钟形。
复合长桁到蒙皮壁板的“附着区域”指长桁附着于壁板的最内侧(相对于长桁)区域，该区域又被称为凸缘。在此陈述的示例性实施例从长桁侧面到长桁腿部具有光滑、宽半径、连续的曲线来最小化或消除任何潜在的带层破损及从填充材料(比如织物或带)基体上分离并最小化过量的树脂积聚。
复合长桁形状的一组非限定的更进一步的示例性实施例如图5-9所示。其它的形状，当然也是可以的并处在本公开的技术范围内。
在图5中，长桁300基本上是抛物线形，具有向下弯曲至侧面304呈凸曲线状的圆顶302。侧面304在切点305从圆顶302过渡到圆顶302曲率而后在宽半径曲线306的切点过渡到长桁腿部308之前沿直线下倾。
图6所示的长桁310具有一个圆形曲线313的基本平坦的顶部312，其中所述圆形曲线313引致侧面314，所述侧面314基本上垂直光滑向下延伸。在该例子中每个侧面314形成一个拐点315。侧面314的低端弯曲穿过一个大半径的转弯318并延伸至腿部316。
图7所示的长桁320可被称为基本上是钟形的，并具有一个带有延伸至侧面324的圆形端部325的基本上平坦的顶部322，该侧面324向下延伸并弯曲穿过一个大半径的转弯328至腿部326。如图所示，侧面324以90°角向下直线延伸到任何角度α角处，其中所述α角可在90°及45°之间变动。
图8所示的长桁340具有一个圆形的顶部342且它基本上为抛物线形或钟形。圆形顶部342以凸曲线向侧面344光滑延伸，该侧面344在向下延伸的同时向外部伸展。侧面344而后穿过一个宽角度曲线345延伸以形成腿部346。如图所示的角α可在约35°到约65°之间变动。
图9所示的长桁350具有一个圆形的顶部352且基本上为抛物线形或钟形，同时相比图8中长桁340，具有直侧面更短总体形状上更圆的形状。圆形顶部352以凸曲率向侧面354光滑延伸，该侧面354在向下延伸的同时向外部伸展。侧面354而后穿过一个宽角度曲线355延伸以形成腿部356。如图所示的角α可在约35°到约65°之间变动。
根据前面的例子，很明显可能存在许多复合长桁形状，而且在目前公开的技术中，只要这些形状包括一个从长桁侧面向腿部的光滑、宽半径的过渡(在一些情况下是从长桁顶部向长桁侧面)来最小化或消除潜在的在过渡点存在过量的树脂积聚、纤维分离、剥离、纤维起皱、波纹或波形(面内波纹)及树脂基体内的气孔。
因为示例性实施例的长桁具有光滑的形状(至少在长桁侧面与长桁腿部及长桁侧面与顶部的结合区域)，可以在实施例中采用带层而非织物预浸材料。带层具有在单一平面内带的每一层。带中的层的取向可使应用一系列优化取向的带来形成长桁成为可能。带层的使用可减少材料费用并提供了减轻重量的潜能。
图10表明了制造成形的复合长桁的方法400的示例性实施例。当然，也可应用其它方法。在此情况下，应用一个外模线工具。在工序410中，需要对在蒙皮壁板、机翼、机身或其它需要用长桁加强的部件上的长桁间距及位置作出决定。一旦决定作出，则在工序420中将部件放置于外模线工具上。而后在工序430中将长桁形状的囊或芯轴置于在之前决定的位置及间隙处的部件上。而后在工序440中准备好带叠层(或其它的复合纤维叠层)。带叠层有一系列有取向的堆叠层，而且带已用合适的树脂，比如环氧树脂进行了预浸渍。在工序450中将带叠层置于囊或芯轴上。此时，在工序460中部件、囊或芯轴及带叠层的组装均在真空袋中进行。在工序470中将袋抽真空，并将带叠层固结在部件上。环氧树脂基体的典型温度可约为350°F，压力约为85psi。其它的树脂需要其它的温度及压力条件。一般来说，但不必要，壁板的树脂及长桁的树脂是相同的。因此，在固结过程中长桁的树脂与壁板的树脂也同时固化或“共同固化”。这有利于在长桁及壁板间形成强的结合，因为树脂流动并固化到包括壁板及长桁填充物的附着区基体中。固结后，在工序480中移走袋子。此时长桁与部件固结。在示例性的工序中，柔性的褶皱带形成一个光滑的弯曲长桁从而最小化长桁中存在结构问题的可能性。该长桁没有急转半径曲线或急的转弯，而具有光滑、连续及宽半径的曲线。进一步地，在一些示例性的实施例中，不要求使用垫板或垫片。这可除去与应用这些装置相关的花费。
尽管至少一个示例性的实施例已在之前的详细描述中说明，需要明白的是还有大量的改动存在。还需明白的是示例性的实施例只是举例，并不意于以任何方式对已描述实施例的范围、适用性及结构进行限制。相反地，之前的详细描述为那些熟悉该技术的人提供了一个方便的路线图来实施这个或这些示例性的实施例。需要理解的是在元件的功能及布置方面可在不背离附加的权利要求及其法律等效物所阐明的范围内作出各种改变。例如，长桁可以在一个分离操作中固化并采用粘结剂在第二步操作时连接于蒙皮。

Claims (19)

1.一种飞行器的加强蒙皮壁板，其包括：
复合飞行器蒙皮壁板(150)；以及
与所述飞行器蒙皮壁板(150)固结的复合长桁(300)，并且
特征在于，所述长桁(300)包括一对长桁侧面(304)，每个长桁侧面(304)均具有拐点(305)，该拐点(305)是从长桁顶部(302)延伸至长桁腿部(308)的平滑转变点，所述长桁侧面(304)各自穿过一个宽半径、光滑连续的曲线(306)延伸至长桁腿部(308)。
2.根据权利要求1所述的加强蒙皮壁板，其中所述复合长桁(300)的顶部的横截面基本为抛物线形或椭圆形。
3.根据权利要求1所述的加强蒙皮壁板，其中所述复合长桁(310)的横截面大体上为钟形。
4.根据权利要求1所述的加强蒙皮壁板，其中所述长桁的顶部包括一个基本上平坦的长桁顶部(322)或凸曲线形状(342)。
5.根据权利要求1所述的加强蒙皮壁板，其中所述拐点位于邻近每个长桁侧面(304)中心的位置。
6.根据权利要求1所述的加强蒙皮壁板，其中所述拐点位于邻近每个长桁侧面(304)的较低位置处。
7.根据权利要求1所述的加强蒙皮壁板，其中所述复合长桁(300)包括固结的堆叠带层，至少一些所述堆叠带层取向为不同的方向。
8.根据权利要求1所述的加强蒙皮壁板，其中所述复合飞行器蒙皮壁板(150)及所述复合长桁(300)包括通用的树脂及填充材料。
9.根据权利要求1所述的加强蒙皮壁板，其还进一步包括含有一部分所述复合长桁(300)及邻近附着在所述复合飞行器蒙皮壁板(150)上长桁点的一部分所述复合飞行器蒙皮壁板(150)的附着区域，该附着区域基本上没有过量的树脂。
10.根据权利要求1所述的加强蒙皮壁板，其还进一步包括含有一部分所述长桁(300)及邻近附着在所述复合飞行器蒙皮壁板(150)上长桁点的一部分所述复合飞行器蒙皮壁板(150)的附着区域，该附着区域基本上没有与所述复合长桁(300)的纤维材料分离且从该复合长桁(300)的纤维材料突出的复合纤维。
11.一种加强的壁板，其包括：
包括复合材料的壁板(150)；
与所述壁板(150)固结的长桁(300)，该长桁(300)包括复合材料，该长桁(300)包括一对长桁侧面(304)，每个长桁侧面(304)均具有拐点(305)，该拐点是从长桁顶部(302)延伸到长桁腿部(308)的平滑转变点；以及
包括一部分所述长桁(300)及一部分所述壁板(150)的附着区域，其中所述一部分所述壁板(150)包括附着到所述壁板(150)的长桁点，该附着区域基本上没有所述长桁(300)的所述复合材料的损坏层。
12.根据权利要求11所述的加强壁板，其中所述长桁(300)的上部的横截面大体上为抛物线形或椭圆形。
13.根据权利要求11所述的加强壁板，其中所述长桁(310)的横截面大体上为钟形。
14.根据权利要求11所述的加强壁板，其中所述长桁(300)包括固结的堆叠带层，至少一些所述堆叠带层取向为不同的方向。
15.根据权利要求11所述的加强壁板，其中所述附着区域没有过量的树脂。
16.根据权利要求11所述的加强壁板，其中所述附着区域没有与所述长桁的纤维材料分离且从该长桁的纤维材料突出的复合纤维。
17.一种用长桁(300)加强复合壁板(150)的方法，该方法包括：
确定与复合壁板固结的长桁的位置及间距；
在模具(200)上对所述复合壁板定位；
在确定的位置及间距处在所述复合壁板上放置符合待形成的所述长桁形状的成形芯轴(120)；
准备复合材料的叠层来形成长桁；
在各所述芯轴上放置准备好的复合材料的叠层；
至少将所述复合壁板及覆盖叠层的芯轴封入一个真空袋内；
在热及压力下将所述长桁固化在所述复合壁板上；而且
制造加强的复合壁板，其中每个所述长桁均包括一对长桁侧面(304)，每个长桁侧面(304)均具有拐点(305)，该拐点是从长桁顶部(302)延伸到长桁腿部(308)的平滑转变点，而且每个长桁侧面均以连续光滑曲线形式延伸到长桁腿部。
18.根据权利要求17所述的方法，其中定位步骤包括在外模线工具中定位。
19.根据权利要求17所述的方法，其中固化步骤包括通过形成没有与所述长桁的纤维材料分离且从该长桁的纤维材料突出的复合纤维以及没有过量树脂的附着区域进行固结。
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