CN104428127A - 自加强复合面板及其制造方法 - Google Patents
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Abstract
本发明提出一种面板的制造方法,所述面板包括外蒙皮和加强筋,所述加强筋包括连接部分(18)以及至少一个突出部分(16),所述方法包括:在至少一个插入件(30)上披覆纤维层(24),从而使各个纤维层(24)包括连接部分(28)和相对于连接部分(28)向下突出的部分(26)的步骤;披覆构成外蒙皮(12)的纤维层(22)的步骤,以及联结所述纤维层(22、24)的步骤。本发明还提出一种实施所述方法的设备。
Description
技术领域
本发明涉及一种制造面板的方法,该面板包括增强其刚度的元件;以及一种用于实施这种方法的设备。
本发明更特别地涉及一种制造以被称为“自加强”型的复合材料制成的面板的方法,所述面板例如被应用于飞行器机身、结构化的箱或飞行器的机翼。
背景技术
自加强面板主要由平面或拱形的外蒙皮构成,与面板的平面相垂直的加强筋附接在所述外蒙皮上,从而能提高此板对于施加于其上的机械应力的抵抗强度。
各个加强筋是长形的元件,其竖直的横截面呈L形、T形或U形。加强筋因此包括与外蒙皮平行且固定在外蒙皮上的水平部分,以及一个或多个垂直于外蒙皮的主平面的纵向竖直部分。
根据一种已知的实施方式,外蒙皮和加强筋以复合材料制成;外蒙皮和加强筋包括以至少一种材料构成的纤维,所述纤维被称为加强纤维,纤维之间通过例如树脂的基质连接。
用于制造这种自加强面板的常规制造方法包括:把外蒙皮定位在模制的支撑件上,随后将用于构成预成型的加强筋的蒙皮放置在外蒙皮上。由此形成的整体被真空袋覆盖,用以允许围绕蒙皮形成气隙。
随后,楔合装置被设置在真空袋上方以便使加强筋的竖直部分保持就位。
组装在烘箱中完成,用以实现树脂的聚合作用。
当实施放置时,外蒙皮以及用于构成加强筋的蒙皮被预先浸渍树脂。
借助预成型件或插入件,对用于构成加强筋的蒙皮进行装配,随后,预成型件或插入件在装配空气袋之前被退回,然后是楔合装置。
在放置楔合装置之前,任何设备都不能正确地保持加强筋的竖直部分。所述加强筋因此可能会变形,且这种变形也存在于完工的面板上。
此外,放置真空袋和楔合装置还可能使加强筋的竖直部分发生变形。
最后,这种方法要求有人员介入支撑件的上方,从而能将不同的元件良好地定位,从而使要制造大尺寸面板的工作变得较为困难。
本发明的目的在于提出一种方法和设备,其允许获得自加强面板,加强筋的竖直部分被正确地平整化以用于所述自加强面板,从而使所述面板的质量得以优化。
发明内容
本发明提出一种自加强复合面板的制造方法,该面板包括外蒙皮和加强筋,各个加强筋包括将加强筋连接至外蒙皮的连接部分,以及相对于连接部分突出的至少一个突出部分,
其特征在于,所述方法包括在与加强筋的最终形状呈互补形的至少一个插入件上披覆用于构成加强筋的纤维层,从而使得用于构成加强筋的各个纤维层包括连接部分和相对于连接部分向下突出的突出部分的步骤,在用于构成加强筋的纤维层上披覆用于构成外蒙皮的纤维层的步骤,以及包括将全部纤维层同时联结的步骤。
将构成加强筋的纤维层的各个竖直部分定位在插入件上使得在联结步骤过程中允许便于保持所述加强筋的形状,从而允许获得包括比较精确的形状的加强筋的面板。
优选地,在所述至少一个插入件上披覆纤维层的步骤之后,接着是把被相关的纤维层覆盖的各个插入件定位在模制的支撑件上的步骤。
优选地,定位加强筋的步骤包括使被纤维层覆盖的插入件以彼此相邻的方式定位。
优选地,纤维层用于通过基质而相互连接,且在披覆和定位的步骤时,纤维层没有被基质浸渍,且联结步骤包括注入所述基质的阶段,以及随后使所述基质固结的阶段。
优选地,基质的注入步骤包括从下向上注入基质。
优选地,联结步骤包括在注入所述基质之前,把脱模织物、排气毛毡、抛光金属板和真空袋之中的至少一个定位在用于构成外蒙皮的纤维层上。
优选地,面板包括固定在加强筋和/或外蒙皮上的金属配件,且所述方法包括在披覆用于构成加强筋的纤维层的步骤的同时装配所述配件的步骤。
本发明还提出一种实施根据本发明的方法的设备,该设备包括模制的支撑件,用于构成加强筋和外蒙皮的纤维层借助插入件被披覆在所述支撑件上,其特征在于,所述设备包括将各个插入件在支撑件上沿纵向和/或横向定位的定位装置。
在模制支撑件上定位插入件,允许获得加强筋的竖直部分的良好的横向定位及平行性。
此外,还可以在同一插入件上使用不同形状和尺寸的插入件,以便制造具有不同尺寸的其它的面板。
优选地,所述定位装置包括键系统。
优选地,支撑件包括水平上表面,所述水平上表面包括与各个插入件的定位装置协作的凹槽,以及纤维层的连接基质的注入孔。
优选地,各个插入件呈平行六面体形,所述平行六面体具有纵向主方向且具有沿横向的竖直面的矩形截面。
优选地,支撑件以具有较小膨胀系数的材料制成。
优选地,各个插入件以具有较大膨胀系数的材料制成。
优选地,所述设备包括将各个配件在支撑件上沿纵向和/或横向定位的定位装置。
附图说明
本发明的其它特征和优点将在阅读以下详细描述后得以体现,为了便于理解这些描述将参考附图,其中:
–图1是包括加强筋的自加强复合面板的立体示意图,且该自加强复合面板是根据本发明而生产的;
–图2是支撑件的示意图,在该支撑件上将被披覆用于构成图1所示的复合面板的纤维层;
–图3是与图2类似的视图,其中,被用于构成加强筋的相关的纤维层覆盖的插入件被定位在支撑件上;
–图4是与图3类似的视图,其中,被其相关的纤维层覆盖的全部插入件都被放置在支撑件上;
–图5是在注入基质之前所述布置的沿横向竖直面的截面图;
–图6是根据本发明制造的包括加强筋和金属配件的自加强复合面板的底视立体示意图。
具体实施方式
为了描述本发明,以非限制性的方式,采用由图1所示的坐标L、V、T表示的纵向、竖直与横向方向。
此外,还采用沿地球重力的方向作为从上到下的方向。将理解的是:坐标L、V、T的竖直方向V可与地球重力方向重合,这是例如以非限制性方式示出的。因此,将理解的是:以将要描述的本发明的变型为例,坐标L、V、T的竖直方向V可相对于沿地球重力的方向倾斜。
在以下描述中,相同、相似或类似的元件将由相同的附图标记指示。
已在图1上示出自加强型的面板10,其包括外蒙皮12和多个加强筋14。
外蒙皮12和加强筋14由复合材料制成,即:其包括以至少一种材料制成的纤维,称为加强纤维,纤维之间通过例如树脂的基质连接。
例如面板10的目的在于构成飞行器的机身或机翼的一部分,外蒙皮12包括位于飞行器的外部的外表面12a,并且加强筋位于飞行器的机身的内部。
在此,面板10呈基本水平的平板的形式,即在横向于纵平面上延伸的平板。应当理解,本发明并不限于这种类型的面板10,其可以由拱形和/或弯曲的板构成。
同样,为了便于理解本发明,面板10被示出为沿着横向于纵向的主方向。将理解的是:面板10可以具有任何其它方向而并不超出本发明的范围。
加强筋14被用来放置在机身的内部,其因此位于面板10的内侧。各个加强筋14还被制造得可包括相对于外蒙皮12的内表面12b向内突出的一部分。
各个加强筋14包括沿纵向主方向延伸的长形元件。由于所述加强筋相对于内蒙皮沿竖直突出,因此,加强筋给外蒙皮12的屈曲提供额外的刚度。
如图1所示,各个加强筋14沿横向竖直面的截面呈L形、T形或U形。各个加强筋14包括将加强筋14连接至外蒙皮的连接部分18,所述连接部分18取向为横向于纵向且与外蒙皮12的内表面12b连结。各个加强筋14还包括至少一个突出部分16,所述至少一个突出部分16在此在纵向上竖直延伸且相对于连接部分18竖直地向下突出,并从与连接部分18相关联的侧边开始远离外蒙皮12。
加强筋14被彼此相邻地设置,其在外蒙皮12上横向分布且在其突出部分16处彼此横向相联。
因此,加强筋14的各个突出部分16被联结在与相邻的加强筋14相联的突出部分16上。此外,具有呈L形截面的加强筋14被设置在面板12的侧向末端处且所述加强筋的唯一的突出部分16被联结在与相邻的加强筋14的相关联的突出部分16上。
在图2上示出支撑件20,面板10在该支撑件上被形成。
所述支撑件20,也被称为“参考平台”,由整体呈水平的平行四边形的元件构成,所述支撑件20包括水平上表面20s,在该上表面上,不同的纤维层被连续地放置,用以构成面板10。
已在图3及随后的图上示出借助实施所述方法的设备来制造面板10的制造方法的连续步骤。
所述面板10是根据如下一种方法制造,所述方法包括披覆,即连续地放置用于构成外蒙皮12和加强筋14的纤维层,随后通过使基质固化而使纤维层之间联结。
根据本发明,在用于构成面板10的外蒙皮的纤维层22之前,披覆用于构成加强筋14的纤维层24。同样,用于构成加强筋14的各个纤维层24被成型为从而具有与其将构成的加强筋14相同的形状。
用于构成加强筋的各个纤维层24因此包括用于构成加强筋14的连接部分18的连接部分28,以及从用于构成加强筋14的突出部分16的相关的连接部分28的一个边缘开始向下突出的至少一个纵向竖直的突出部分26。
为了在放置用于构成其它的加强筋14和外蒙皮12的其它纤维层22、24的之后的操作过程中,以及在使纤维层相互连结的步骤中使各个纤维层24保持形状,所述设备包括插入件30,在该插入件30上披覆有用于构成加强筋14的所述纤维层24。
所述插入件30的形状与待获得的加强筋14的最终形状互补,在这里换言之,插入件30沿横向竖直面是矩形的截面。插入件30因此包括水平上壁32,在该上壁32上设有纤维层24的连接部分28;以及两个纵向竖直的侧壁34,纤维层24的突出部分26抵靠所述各个侧壁而被联结。
优选地,纤维层24在插入件30被放置在支撑件20之前,被放置在插入件30上。这允许更有效地披覆纤维层24,因为插入件30从而对于操作人员而言更易接近。此外,纤维层24仅通过重力作用而在插入件30上被保持到位,因此不需要任何额外的保持装置。
由插入件30和纤维层24构成的整体被放置在支撑件20上。
支撑件20和插入件30包括允许使插入件30相对于支撑件20水平定位、且因此使纤维层24相对于支撑件20水平定位的装置。
这些定位装置在此包括定位键,所述定位键被容纳在支撑件20中所制造的补充凹槽36中,且各个插入件30沿纵向抵靠这些定位键。
面板10的制造方法包括如下步骤,包括连续披覆用于构成加强筋14的纤维层24,这通过把组件一组接一组定位在支撑件20上而实现,所述各个组件由插入件30和相关的纤维层24构成。进行这种连续的放置,需要把组件以彼此接邻的方式定位在支撑件20上,也就是说,把每个组件定位在已经放置好的组件的一侧。
当相邻的两个组件被放置在支撑件20上时,其插入件30分别被相对于彼此横向错开,且这两个相邻的插入件30之间的横向距离“e”对应于加强筋14的最终宽度。
各自分别属于纤维层24的两个竖直部分26,被设置在两个相邻的插入件30之间。
根据一种优选的实施方式,两个相邻的插入件30之间的横向距离“e”被确定成使得纤维层24的两个竖直部分26被横向夹紧在两个插入件30之间。
在放置步骤结束后,正如在图4可见,用于构成加强筋14的纤维层24的整体被放置在支撑件20上,且借助插入件30,各自被保持成为相关联的加强筋14的最终形状。
根据插入件30的另一方面,插入件30被制造成使得用以使纤维层24的全部的连接部分28都位于距离支撑件的上表面20s相同的竖直距离处,即纤维层24的全部的连接部分28都位于同一水平平面。
随后,根据之后的步骤,用于构成外蒙皮12的纤维层22被披覆在支撑件20上,从而覆盖用于构成加强筋14的蒙皮,即覆盖用于构成加强筋14的纤维层24的连接部分28。
正如上文所述,连接部分28都位于相同的水平面。其因此又确定水平平面,用于构成外蒙皮12的纤维层22被披覆在所述水平平面上。
在之后的这一步骤完成后,用于构成面板10的纤维层22、24整体都被放置在支撑件20上。用于构成加强筋14的纤维层24的各个竖直部分向下延伸且被重力保持在此构型中。因此不存在在所述方法的随后部分中发生变形的风险。
对于用于构成外蒙皮12的纤维层22而言亦是如此,所述外蒙皮12通过地球重力自然地向下压靠在纤维层24的连接部分28上。如图5所示,纤维层22、24随后被不同的周围材料层覆盖,所述周围材料层将在之后的纤维层22、24的联结步骤中被使用。
这些周围材料层尤其包括设置在组件外部的真空袋40、便于脱模的织物42、排空织物或毛毡44,以及用于在真空袋40下方形成真空的系统46,和用于改善外蒙皮12的外表面12a的表面状态的抛光金属板“cal plate(垫板)”47。
所述方法包括以下的联结纤维以获得面板的步骤。
所述步骤包括注入树脂,用以把不同层22、24的纤维在彼此之间连接,并将纤维层22、24整体连接。
从支撑件20由下向上注入树脂。因此,纤维层22、24由其突出部分26的下方自由端开始,直到用于构成外蒙皮12的纤维层22都被浸渍,这通过流入两个相邻的插入件30之间,进入位于由其相互面对的侧壁34所限定的空间中而实现,在所述两个侧壁之间容纳有纤维层24的竖直部分26。
为此,支撑件20包括树脂的注入孔48,该注入孔48通向支撑件20的水平上表面20s。优选地,这些孔通向凹槽36,从而允许插入件30在支撑件20上的横向定位。
正如图3所示,限定凹槽36在支撑件20上的定位,用以使与插入件30协作的定位键位于插入件30的侧壁34处。因此,纵向凹槽36横向位于纤维层24的突出的竖直部分26处。
在树脂被完全注入且已经去除空气之后,树脂例如在烘箱中固化。
根据所述设备的另一方面,支撑件20由具有较小热膨胀系数的材料制成,这允许限制其尺寸的变化。举例而言,支撑件20的构成材料是已知名为“因钢”的铁镍合金。此外,插入件30由具有相对较高的热膨胀系数的材料制成,例如铝。
这允许插入件30与完工的面板10方便地分离与脱模,尽管插入件30与由此获得的加强筋14之间面对面的支撑竖直面具有竖直的取向亦是如此。因此不再需要用起模斜度角(angle de dépouille)来制造加强筋14和插入件30。
根据自加强面板10的一种变型实施方式,其包括在其制造过程中与面板10形成一体的金属配件50。
这些金属配件50,例如压缩金属配件,尤其允许形成飞行器的部件可随后放置于其上的支撑件。
根据该变型实施方式,在放置纤维层22、24的步骤同时,且优选地,在插入件30上放置用于构成加强筋14的纤维层24的步骤同时,配件50被放置在插入件30或特殊的插入件上。插入件30适于承载配件50,用以使配件50相对于纤维层22、24且相对于支撑件20而定位。仍然根据另一变型实施方式,各个插入件30包括适于局部容纳配件50的凹部(未示出)。
在此,正如图6所示,各个配件50由压缩金属配件构成,其包括横向纵壁52,所述横向纵壁52位于与相关的加强筋14的连接部分18相同的平面内;两个竖直的纵向侧部54,所述两个竖直的纵向侧部54各自位于加强筋14的突出部分16的平面内,以及横向竖直部分56,所述横向竖直部分56与金属配件50的其它部分52、54的纵向端相连。
金属配件50在此位于面板10的纵向端处。
因此,在装配时,金属配件50覆盖相关的插入件30的纵向端。
应当理解的是:本发明不仅仅局限于仅包括具有竖直的纵向的突出部分16的加强筋14的面板10,还可包括具有横向竖直突出部分的加强筋14的面板。
包括所述加强筋14的面板的制造方法与刚才描述的方法类似,且所述设备适于这些横向的竖直突出部分。
为此,所述设备包括多个纵向排齐的插入件30,所述插入件30沿纵向被错开,从而允许构成横向竖直的突出部分。
插入件还包括图2所示的横向凹槽60,所述横向凹槽60允许获得插入件20在支撑件30上的纵向定位,且在其中,开通了用于注入树脂的所述注入孔。
Claims (12)
1.一种自加强复合面板(10)的制造方法,所述面板包括外蒙皮(12)和加强筋(14),各个加强筋(14)包括将所述加强筋(14)连接至所述外蒙皮(12)的连接部分(18)和至少一个从所述连接部分(18)突出的突出部分(16),所述方法包括:
在具有与所述加强筋(14)的最终形状互补的形状的至少一个插入件(30)上披覆用于形成所述加强筋(14)的纤维层(24),从而使得用于构成加强筋(14)的各个纤维层(24)包括连接部分(28)和从所述连接部分(28)向下突出的突出部分(26)的步骤,
在用于构成所述加强筋(14)的纤维层(24)上披覆用于构成所述外蒙皮(12)的纤维层(22)的步骤,
利用基质将全部所述纤维层(22、24)同时地联结的步骤,
其中,在披覆和定位步骤中,所述纤维层(22、24)没有被基质浸渍,且联结步骤包括注入所述基质的阶段,以及随后使所述基质固化的阶段,且其中,注入所述基质的步骤包括从下向上注入基质。
2.根据权利要求1所述的方法,其特征在于,在所述至少一个插入件(30)上披覆纤维层(24)的步骤之后,接着是把被相关的纤维层(24)覆盖的各个插入件(30)定位在模制的支撑件(20)上的步骤。
3.根据权利要求2所述的方法,其特征在于,定位步骤包括把由纤维层(24)覆盖的插入件(30)以彼此相邻的方式定位。
4.根据权利要求1至3中任一项所述的方法,其特征在于,联结步骤包括在注入所述基质的阶段之前,把脱模织物(42)、排气毛毡(44)、抛光金属板(47)和真空袋(40)之中的至少一个定位在用于构成所述外蒙皮(12)的纤维层(22)上。
5.根据权利要求1至4中任一项所述的方法,其中,所述面板(10)包括固定至所述加强筋(14)和/或所述外蒙皮(12)的金属的配件(50),其特征在于,所述方法包括与披覆用于构成所述加强筋(14)的纤维层(24)的步骤同时地安装所述配件(50)的步骤。
6.一种用于实施根据权利要求1至5中任一项所述的方法的设备,所述设备包括模制的支撑件(20),利用插入件(30)在所述支撑件(20)上披覆用于构成所述加强筋(14)和外蒙皮(12)的纤维层(22、24),其特征在于,所述设备包括将各个插入件(30)在所述支撑件(20)上沿纵向和/或沿横向定位的定位装置(36)。
7.根据权利要求6所述的设备,其特征在于,所述定位装置(36)由键系统构成。
8.根据权利要求6或7中任一项所述的设备,其特征在于,所述支撑件(20)包括水平上表面(20s),所述水平上表面(20s)包括与各个插入件(30)的定位装置协作的凹槽(36)、以及连接纤维层(22、24)的基质的注入孔(48)。
9.根据权利要求6至8中任一项所述的设备,其特征在于,各个插入件(30)呈平行六面体形,该平行六面体具有沿纵向的主方向且具有沿横向的竖直面的矩形截面。
10.根据权利要求6至9中任一项所述的设备,其特征在于,所述支撑件(20)由具有较小膨胀系数的材料制成。
11.根据权利要求6至10中任一项所述的设备,其特征在于,各个插入件(30)由具有较大膨胀系数的材料制成。
12.根据权利要求6至11中任一项并结合权利要求5所述的设备,其特征在于,所述设备包括将各个配件(50)在支撑件(20)上沿纵向和/或沿横向定位的定位装置。
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1254925 | 2012-05-29 | ||
FR1254925A FR2991228B1 (fr) | 2012-05-29 | 2012-05-29 | Procede et dispositif de realisation d'un panneau composite auto-raidi |
PCT/FR2013/051159 WO2013178917A1 (fr) | 2012-05-29 | 2013-05-27 | Panneau composite auto-raidi et procede de realisation |
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CN (1) | CN104428127A (zh) |
CA (1) | CA2874937C (zh) |
FR (1) | FR2991228B1 (zh) |
GB (1) | GB2520438B (zh) |
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CN110494274A (zh) * | 2017-03-28 | 2019-11-22 | 劳斯莱斯股份有限公司 | 用于制造复合部件的工具 |
CN110978536A (zh) * | 2019-10-29 | 2020-04-10 | 莆田市子都贸易有限公司 | 一种塑胶件热保压设备 |
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FR3015347B1 (fr) * | 2013-12-19 | 2016-06-24 | Aerolia | Dispositif et procede de fabrication d'un panneau auto-raidi en materiau composite |
CN105619833B (zh) * | 2014-10-28 | 2018-03-02 | 哈尔滨飞机工业集团有限责任公司 | 一种防止蜂窝回缩的成型方法 |
US20210237370A1 (en) * | 2020-02-04 | 2021-08-05 | The Boeing Company | Composite Assembly with Integrally Formed Panels and Stiffeners |
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2012
- 2012-05-29 FR FR1254925A patent/FR2991228B1/fr active Active
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2013
- 2013-05-27 CA CA2874937A patent/CA2874937C/fr active Active
- 2013-05-27 RU RU2014152719A patent/RU2014152719A/ru not_active Application Discontinuation
- 2013-05-27 CN CN201380034292.4A patent/CN104428127A/zh active Pending
- 2013-05-27 GB GB1421210.4A patent/GB2520438B/en active Active
- 2013-05-27 WO PCT/FR2013/051159 patent/WO2013178917A1/fr active Application Filing
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Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN105415700A (zh) * | 2015-11-30 | 2016-03-23 | 哈尔滨飞机工业集团有限责任公司 | 一种用于曲面的工艺垫板使用方法 |
CN110494274A (zh) * | 2017-03-28 | 2019-11-22 | 劳斯莱斯股份有限公司 | 用于制造复合部件的工具 |
CN110494274B (zh) * | 2017-03-28 | 2022-04-08 | 劳斯莱斯股份有限公司 | 用于制造复合部件的工具 |
CN110978536A (zh) * | 2019-10-29 | 2020-04-10 | 莆田市子都贸易有限公司 | 一种塑胶件热保压设备 |
CN110978536B (zh) * | 2019-10-29 | 2021-12-17 | 泰兴市康威塑业有限公司 | 一种塑胶件热保压设备 |
Also Published As
Publication number | Publication date |
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FR2991228B1 (fr) | 2015-03-06 |
GB2520438A (en) | 2015-05-20 |
CA2874937C (fr) | 2021-02-16 |
US20150165744A1 (en) | 2015-06-18 |
RU2014152719A (ru) | 2016-07-20 |
GB201421210D0 (en) | 2015-01-14 |
FR2991228A1 (fr) | 2013-12-06 |
CA2874937A1 (fr) | 2013-12-05 |
WO2013178917A1 (fr) | 2013-12-05 |
US10105938B2 (en) | 2018-10-23 |
GB2520438B (en) | 2017-07-26 |
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