CN102470613A - 层压复合材料棒、制造方法和在复合材料结构中的用途 - Google Patents

层压复合材料棒、制造方法和在复合材料结构中的用途 Download PDF

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Publication number
CN102470613A
CN102470613A CN2010800363128A CN201080036312A CN102470613A CN 102470613 A CN102470613 A CN 102470613A CN 2010800363128 A CN2010800363128 A CN 2010800363128A CN 201080036312 A CN201080036312 A CN 201080036312A CN 102470613 A CN102470613 A CN 102470613A
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China
Prior art keywords
rod
composite
plate
laminar composite
laminar
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CN2010800363128A
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English (en)
Inventor
D·A·弗里希
M·J·皮耶
K·S·丘本-艾尔特兰
K·卡吉塔
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Boeing Co
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Boeing Co
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Publication of CN102470613A publication Critical patent/CN102470613A/zh
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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Ceramic Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Textile Engineering (AREA)
  • Composite Materials (AREA)
  • Moulding By Coating Moulds (AREA)
  • Laminated Bodies (AREA)

Abstract

层压复合材料棒(16)包括棒体，该棒体具有大体上圆形或椭圆形的横截面，并包括相对于彼此以不同朝向放置的多个层压复合材料层(1)。

Description

层压复合材料棒、制造方法和在复合材料结构中的用途
技术领域
本公开涉及增强结构板纵梁的结构棒。更具体地，本公开涉及预固化的层压复合材料棒和层压复合材料棒的制造方法，该层压复合材料棒适于在纵梁的树脂注入和固化期间支撑结构板纵梁，并且该层压复合材料棒可被调整以满足设计要求并通过提供降低的热膨胀系数降低板纵梁中的热应力。
背景技术
PRSEUS(拉挤成型的棒缝合有效结构)结构设计理念可要求棒在纵梁的组装、注入和固化期间支撑板纵梁。在目前板纵梁设计中使用的棒可由产生具有全部零度朝向纤维的棒的拉挤成型方法制造。该方法可产生具有高于大多数设计情况下所要求的刚度和热膨胀系数的棒。沿纵向的零度纤维可承受直径膨胀，而并不对在固化期间棒直径方向的树脂膨胀提供约束。棒的该结构可产生高残余固化应力并导致棒和外壳层(wrap ply)之间的层中的树脂破裂。
已提出的改进拉挤成型棒的方法包括用纤维螺旋状包裹棒，所述纤维意欲部分约束树脂膨胀。然而这些解决方法可能仅去除小部分的零度纤维并且大大增加了拉挤成型棒的部分成本。此外，现有拉挤成型棒的设计可伴随板纵梁的棒与外壳界面中的残余应力。
传统拉挤成型的棒可由全部零度纤维形成，并且因此可非常坚硬，调整性质以满足不同要求的可修改性很小。另外，由于100％零度占主导的结构，拉挤成型的棒可显示非常高的热膨胀系数。
因此，需要如此预固化的层压复合材料棒，该棒适于在树脂注入和纵梁固化期间支撑结构板纵梁，并且该棒可被调整以满足设计要求并通过提供降低的热膨胀系数降低板纵梁中的热应力。
发明内容
一般而言，本公开涉及层压复合材料棒。层压复合材料棒的说明性实施方式包括棒体，该棒体具有大体上圆形或椭圆形的横截面，并包括相对于彼此以不同朝向放置的多个层压复合材料层。
一般而言，本公开进一步涉及棒缝合有效复合材料结构，该结构包括缝合的复合材料结构和预固化的层压复合材料棒，该棒具有大体上圆形或椭圆形的横截面并被并入缝合的复合材料结构。
一般而言，本公开进一步涉及层压复合材料棒制造方法。该方法的说明性实施方式包括提供多个复合材料层，通过放下复合材料层形成层压复合材料板，固化层压复合材料板和由层压复合材料板形成具有大体上圆形或椭圆形的横截面的层压复合材料棒。
在一些实施方式中，棒缝合有效复合材料结构包括表层板(skinpanel)组件；包括棒体的预固化的层压复合材料棒，该棒体包括不含拉挤成型层的多个层压复合材料层，所述层压复合材料层选自石墨带、环氧树脂带和预浸材料，并在棒体中相对于彼此以不同的朝向放置；和棒缝合有效结构板组件，该组件包括一对邻近的纵梁板、连接纵梁板并在层压复合材料棒周围延伸的板外壳和从纵梁板延伸并被缝合至表层板组件上的一对板法兰(panel flange)。
在一些实施方式中，棒缝合有效复合材料结构可包括表层板组件；包括棒体的预固化的层压复合材料棒，该棒体包括不含拉挤成型层的多个层压复合材料层，所述层压复合材料层选自石墨带、环氧树脂带和预浸材料，并在棒体中相对于彼此以不同的朝向放置；和棒缝合有效结构板组件，该组件包括一对邻近的纵梁板、连接纵梁板并在层压复合材料棒周围延伸的板外壳和从纵梁板延伸并被缝合至表层板组件上的一对板法兰。
在一些实施方式中，层压复合材料棒制造方法可包括提供多个复合材料层，所述多个复合材料层选自石墨带、环氧树脂带和预浸材料并不含拉挤成型的层；通过放下相对于彼此处于不同朝向的复合材料层形成层压复合材料板；固化层压复合材料板；通过切割和用机器加工层压复合材料板，由层压复合材料板形成层压复合材料棒；使层压复合材料棒经历表面磨蚀；提供棒缝合有效结构板组件，其包括一对邻近的纵梁板、连接纵梁板的板外壳和从纵梁板延伸的一对板法兰；将层压复合材料棒***纵梁的板外壳中；提供表层板组件；将该对纵梁的板法兰缝合到表层板组件；将树脂注入纵梁；和固化纵梁。
附图说明
图1为用于制造层压复合材料棒的说明性实施方式的层压复合材料板结构中多个层的分解侧视图。
图2为层压复合材料板的边视图。
图3为层压复合材料板的顶视图。
图4为在用于固化的高压釜中被真空密封的层压复合材料板的示意图。
图5为层压复合材料棒的说明性实施方式的透视图。
图6为层压复合材料棒的说明性实施方式的端视图。
图7为被附接到表层板组件上的板组件纵梁的端视图，并且其中***说明性实施方式的层压复合材料棒。
图8为层压复合材料棒制造方法的说明性实施方式的流程图。
图9为航空器生产和服务方法的流程图。
图10为航空器的方块图。
发明详述
以下详细描述在性质上仅是示例性的，并不意欲限制所描述的实施方式或申请和所描述实施方式的应用。如在此所用的，词“示例性的”或“说明性的”表示“用作例子、实例或例证”。任何在此描述为“示例性的”或“说明性的”的实施不必被解释为优于其他实施的优选的或有利的。所有以下所描述的实施是使本领域技术人员能够实践本公开所提供的示例性实施，其并不意欲限制权利要求的范围。此外，不意欲被在前面的技术领域、背景技术、发明内容或以下发明详述中存在的任何表达或暗示的理论所限制。
首先参考图1-6，显示了制造层压复合材料棒16(图6)的说明性实施方式。如图1所示，层压复合材料棒16可包括大体上细长的棒体17，其可具有大体上圆形或椭圆形的横截面形状。通过开始将多个复合材料层1放到叠层工具2上形成扁平的层压复合材料板6(图2和3)——其将最终形成层压复合材料棒16，制造层压复合材料棒16的棒体17。每个层1都可以例如且非限制性地为石墨带或环氧树脂带或其他预浸材料，并且可不含拉挤成型的纤维。取决于层压复合材料棒16的刚度要求，层1可以以不同角度或朝向放置，以形成层压复合材料板6。层压复合材料棒16的刚度和其他性质可通过改变层1的数量以及当它们被放置形成层压复合材料板6时层1相对于彼此的角度或朝向进行调整。例如且非限制性地，在一些实施方式中，层1可以以+45、0、90、0、90和-45度的连续方向布置的顺序放置。
如图4所示，具有以不同角度放置的选择数量的层1的层压复合材料板6随后可例如通过将层压复合材料板6放置在高压釜10中的板支撑物11上进行固化。可通过用密封带13将真空装袋12固定在层压复合材料板6的周边周围，将层压复合材料板6密封在板支撑物11。层压复合材料板6可利用本领域技术人员已知的标准加工技术和参数进行固化。
在其被固化后，层压复合材料板6可经历粗略切割，以大体上将层压复合材料板6的形状转变为层压复合材料棒16的形状。可利用本领域技术人员已知的水喷射技术或合适的可选技术实现层压复合材料板6的粗略切割。层压复合材料板6可随后用机器加工成最终期望形状的层压复合材料棒16。在一些实施方式中，用机器加工的层压复合材料棒16可经历表面磨蚀和/或其他表面制备处理。如图6所示，所完成的层压复合材料棒16可包括放置到层压复合材料板6中的层1(图2)。
如图7所示，例如且非限制性地，所完成的层压复合材料棒16可随后被***缝合的复合材料结构例如PRSEUS(拉挤成型的棒缝合有效结构)板组件纵梁20。板组件纵梁20可为复合织物材料，其包括一对邻近的折叠纵梁板21，从该对邻近的折叠纵梁板21分别延伸一对板法兰24。板外壳22可连接纵梁板21。板外壳22可在层压复合材料棒16周围延伸，以便板外壳22大体上贴合层压复合材料板16的几何形状。板外壳22可在棒与外壳界面23处接触层压复合材料板16。纵梁板21、板外壳22和板法兰24可形成一个连续的件。
板组件纵梁20的板法兰24可被附接到表层板组件30上。在一些实施方式中，板组件纵梁20可被附接到基板26上，基板26可被附接到表层板组件30上。缝合物25可用于将邻近的纵梁板21相互附接，并将板法兰24附接到表层板组件30上。在将板组件纵梁20附接到表层板组件30后，可将板组件纵梁20置于真空袋(未示出)中。可将树脂(未示出)注入板组件纵梁20的织物中，随后可固化板组件纵梁20。
层压复合材料棒16可被调整，以匹配不同的结构要求并大大降低预固化的层压复合材料棒16和板组件纵梁20的周围注入织物部分之间的热膨胀系数(CTE)。此外，由于层压复合材料棒16的低CTE，残余应力可在板组件纵梁20的固化期间被大大降低，这降低或消除了板组件纵梁20的棒与外壳界面23处的界面破裂。可通过改变被放置以制造层压复合材料棒16的层压复合材料板6的数量、顺序和朝向(图2和3)，为具体结构应用设计具有可调整强度和刚度特性的层压复合材料棒16，如在此之前所描述的。
接下来参考图8，显示了层压复合材料棒制造方法的说明性实施方式的流程图800。在方块802中，可放下复合材料层以形成层压复合材料板。例如且非限制性地，每个层都可为石墨带或环氧树脂带或其他预浸材料。可通过改变层数和放下层以形成层压复合材料板的角度，控制层压复合材料板的刚度和其他特性。
在方块804中，可利用真空装袋，在高压釜中密封层压复合材料板。在方块806中，可固化层压复合材料板。在方块808中，层压复合材料板可经历粗略切割过程，其中层压复合材料板被切割成层压复合材料棒的大体构造。可利用水喷射或其他切割过程实施粗略切割过程。在方块810中，层压复合材料板可用机器进行加工，以形成层压复合材料棒。在方块812中，层压复合材料棒可经历表面磨蚀和/或其他表面制备技术。
在方块814中，层压复合材料棒可被***板组件纵梁。在方块816中，板组件纵梁的织物板法兰可被缝合或以其他方式被附接到表层板组件上。在方块818中，可将板组件纵梁密封在真空装袋中。在方块820中，可将树脂注入板组件纵梁的板织物中。在方块822中，可固化板组件纵梁。
接下来参考图9和10，本公开的实施方式可如图9所示在航空器制造和服务方法78和如图10所示在航空器94的情况中使用。在生产前期间，示例性的方法78可包括航空器94的规格和设计80和材料获得82。在生产期间，进行航空器94的部件和子组件制造84和***整合86。此后，航空器94可以经历发照和交货88以进行使用90。在客户使用的同时，航空器94可以被安排进行日常维护和保养92(其也可以包括改进、重新配置、整修等)。
可以由***整合者、第三方和/或操作者(例如用户)进行或执行方法78的每个过程。对本说明书的目的，***整合者可以非限制性地包括诸多航空器制造商和主要***转包商；第三方可以非限制性地包括诸多销售商、转包商和供应商；以及操作者可以是航空公司、租赁公司、军事实体、服务组织等。
如图10所示，通过示例性方法78生产的航空器94可以包括带有多个***96的机体98和内部100。高水平的***96的例子包括一个或多个推进***102、电力***104、水压***106和环境***108。可以包括许多其它***。尽管显示了航空实例，但是本发明的原理可以应用于其它工业，如汽车工业。
本文实施的设备可以在生产和服务方法78的任意一个或多个阶段期间使用。例如，相应于生产过程84的部件和子组件可以被以类似于使用航空器94时生产的部件和子组件的方式进行构造或制造。同样，例如，通过显著加速航空器94的组装或减少航空器94的成本，在生产阶段84和86可以使用一种或多种设备实施方式。类似地，在使用航空器94时，一种或多种设备实施方式可以例如但不限于用于维护和保养92。
尽管本公开的实施方式已就某些示例性实施方式进行了描述，但是应当理解，具体实施方式是用于阐述目的并且是非限制性的，本领域技术人员可以想到其它变化。

Claims (20)

1.一种层压复合材料棒，包括：
棒体，所述棒体具有大体上圆形或椭圆形的横截面，并包括相对于彼此以不同朝向放置的多个层压复合材料层。
2.根据权利要求1所述的层压复合材料棒，其中所述层压复合材料层不含拉挤成型的复合材料层。
3.根据权利要求1所述的层压复合材料棒，其中所述多个层压复合材料层为石墨带、环氧树脂带或预浸材料。
4.一种棒缝合有效复合材料结构，包括：
缝合的复合材料结构；和
预固化的层压复合材料棒，其具有大体上圆形或椭圆形的横截面并被并入所述缝合的复合材料结构。
5.根据权利要求4所述的棒缝合有效复合材料结构，其中所述层压复合材料棒不含拉挤成型的复合材料层。
6.根据权利要求5所述的棒缝合有效复合材料结构，其中所述层压复合材料棒包括相对于彼此以不同朝向放置的多个层压复合材料层。
7.根据权利要求6所述的棒缝合有效复合材料结构，其中所述多个层压复合材料层为石墨带、环氧树脂带或预浸材料。
8.根据权利要求4所述的棒缝合有效复合材料结构，其中所述缝合的复合材料结构包括拉挤成型的棒缝合有效结构板组件纵梁。
9.根据权利要求8所述的棒缝合有效复合材料结构，其中所述纵梁包括一对邻近的纵梁板和板外壳，所述板外壳连接所述纵梁板，并在所述层压复合材料棒周围延伸。
10.根据权利要求9所述的棒缝合有效复合材料结构，进一步包括表层板组件和一对分别从所述纵梁的所述纵梁板处延伸并附接到所述表层板组件上的板法兰。
11.根据权利要求10所述的棒缝合有效复合材料结构，进一步包括将所述纵梁的所述纵梁板彼此附接和将所述板法兰附接到所述表层板组件上的缝合物。
12.一种层压复合材料棒制造方法，包括：
提供多个复合材料层；
通过放下所述复合材料层，形成层压复合材料板；
固化所述层压复合材料板；和
由所述层压复合材料板形成具有大体上圆形或椭圆形横截面的层压复合材料棒。
13.根据权利要求12所述的方法，其中所述提供多个复合材料层包括提供石墨带、环氧树脂带或预浸材料。
14.根据权利要求12所述的方法，其中所述放下所述复合材料层包括以相对于彼此的不同朝向放下所述复合材料层。
15.根据权利要求12所述的方法，其中所述由所述层压复合材料板形成层压复合材料棒包括粗略切割和用机器加工所述层压复合材料板。
16.根据权利要求12所述的方法，进一步包括使所述层压复合棒经历表面磨蚀。
17.根据权利要求16所述的方法，进一步包括提供缝合的复合材料结构并将所述层压复合材料棒***所述缝合的复合材料结构。
18.根据权利要求17所述的方法，进一步包括固化所述缝合的复合材料结构。
19.根据权利要求17所述的方法，其中所述提供缝合的复合材料结构并将所述层压复合材料棒***所述缝合的复合材料结构包括提供拉挤成型的棒缝合有效结构板组件纵梁，并将所述层压复合材料棒***所述纵梁。
20.根据权利要求19所述的方法，进一步包括提供表层板组件并将所述纵梁附接到所述表层板组件上。
CN2010800363128A 2009-08-17 2010-07-14 层压复合材料棒、制造方法和在复合材料结构中的用途 Pending CN102470613A (zh)

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