CN1052680C - 翼型结构的成形方法和装置 - Google Patents

翼型结构的成形方法和装置 Download PDF

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CN1052680C
CN1052680C CN95195368A CN95195368A CN1052680C CN 1052680 C CN1052680 C CN 1052680C CN 95195368 A CN95195368 A CN 95195368A CN 95195368 A CN95195368 A CN 95195368A CN 1052680 C CN1052680 C CN 1052680C
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caul
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W·C·雷恩菲尔德
D·A·科瓦尔斯基
C·D·琼斯
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Abstract

在模制组件(22)中将玻璃纤维或其他材料的包壳贴敷到组合机翼结构(2)上，所述模制组件具有限定机翼下表面形状的部分是柔性的均衡压力用覆盖板组件。该均衡压力用覆盖板构件包括基本上是刚性的，盖住机翼前缘(16)的第一部分(34)。该均衡压力用覆盖板构件的刚性部分改进了对着机翼前缘的机翼包壳的构造。该均衡压力用覆盖板还包括盖住并限定机翼下表面的后缘形状的柔性部分(36)。均衡压力用覆盖板构件的刚度有一个中间连接其刚性和柔性部分的刚度变化的区域(38)。在均衡压力用覆盖板上应用刚性和柔性部分使得可以控制包壳与机翼前缘的一致性，同时，即使机翼内部工作组件尺寸有变化，也可以使包壳与翼的其余部分准确地一致。

Description

翼型结构的成形方法和装置
技术领域
本发明涉及，组合连接如直升飞机旋翼等的翼型结构的方法和装置。
背景技术
现代机翼部件，象直升飞机旋翼、襟翼和副翼等，包括有内部构件，例如旋翼梁的结构支撑构件，机翼成形蜂窝结构构件等。这些机翼部件包括形成机翼外皮的外包壳，而且一般是由浸渍了树脂基体(通常为环氧树脂)的数层玻璃纤维或石墨制成，此浸渍过程在工业上称之为“预浸处理”。机翼内部构件预先组装然后定位在一模制组件中，此模制组件将外包壳固定粘结到机翼内构件上。模制组件包括相互配合的两个半模：其中之一是钢体模件，它有与希望的机翼上或下表面形状一致的内腔；和一互补的均衡压力用覆盖板件，它的内腔与希望的机翼下或上表面形状一致。钢模用于轮廓要求最严格的翼型部分，这部分往往是机翼的上部。
在成形象直升飞机构件这样的复合材料产品方面的最新开发介绍了各种形状模制组件的应用，这种模制组件包括钢制刚性模件，和能使模制工艺改进的相配的柔性均衡压力用覆盖板件。1991，12，10授与A.C.Dublinski等的美国专利5,071,338，1992，2，11授与R.J.Simkulak等的美国专利5,087,187和1992，10，6授与P.B.Leoni等的美国专利5,152,949均介绍了使用有刚性模件和互补柔性均衡压力用覆盖板件的模制组件成形模制复合材料产品的方法和工具。该柔性均衡压力用覆盖板件被建议用于被制造产品的复杂细节部分(专利5,071,338)；并用于用模制产品固化后，使之容易把模制组件从模制产品剥离出来(专利5,152,949)。在上述每一专利中介绍的模制件直升飞机构件。
利用包括有向相邻的工件表面施加不同值的连接压力的可膨胀的工具的模制组件是已知的技术。美国专利3,305,420介绍了一种这样的可膨胀工具，该工具包括一个大扁的可膨胀压力袋和一个或多个小的可膨胀压力袋。大的袋子是由被橡胶或硫化材料浸渍和涂覆的玻璃纤维织物强化叠合层制的。小袋具有相似结构位于可膨胀大压力袋的中空压力腔中。可膨胀小压力袋的中空压力腔充以高压空气，而可膨胀大压力袋的中空压力腔充以低压空气。
发明内容
本发明涉及用于将直升飞机等的机翼，如直升飞机旋翼等的外包壳和翼型内结构构件组装的模制组件的应用。本发明的模制组件包括最好是由钢制成的刚性模体，其内表面确定出翼型上表面形状。该模制组件还包括互补的均衡压力用覆盖板，它的内表面确定出翼型下表面形状。这个均衡压力用覆盖板有一沿覆盖板整个长度上基本是刚性的前缘部；和一相对的后缘部，均衡压力用覆盖板也包括一中间连接该板前缘部和后缘部，刚度减弱的中间部。
均衡压力用覆盖板的基本刚性的前缘部，强制使机翼的前缘与围绕机翼梁和其他内部构件周围的相对精密预定形状一致，提供产生精密机翼表面的能力。同时，均衡压力用覆盖板的柔性后缘部，容纳所有在容限范围内翼梁的蜂窝状芯后部加工中产生的尺寸变异，同时又沿机翼后部保持均匀的压力。
均衡压力用覆盖板最好由预浸渍的玻璃纤维或石墨复合材料布层叠合而成。该布层用诸如可经受固化温度的环氧树脂等树脂预浸渍，彼此层状粘结形成此所述的覆盖板。均衡压力用覆盖板的刚性前缘部最好比柔性后缘部具有较多数目的预浸处理复合材料层数，以便覆盖板的每一部分达到所要的刚度。覆盖板各边缘部相对的刚度和柔性直接与贴敷和粘结到机翼结构上玻璃纤维包壳刚度相关。该覆盖板的柔性边缘部最好比机翼包壳刚度约大6倍。覆盖板刚性端部应至少具有柔性边缘部两倍的刚度。
因此本发明的目的是提供一种组装粘合机翼结构的方法和装置，使前缘被模制成精密的机翼形状，而后缘柔性地连接到蜂窝芯上。前缘部内部组件，通过改变粘结厚度可调整成精密的形状。后缘形状顺从于芯部轮廓，有均匀粘结厚度。
本发明的另一目的是提供一种有如此特征的方法和装置，即，在机翼构件包壳的前缘严格地被机翼其余部分所限制，产生机翼的精密前缘形状。
本发明的还一目的是提供具有如此特征的方法和装置，即，机翼包壳后缘柔顺地贴在芯部，在机翼整个后缘上压力是均匀的。
本发明的再一目的是提供具有如此特征的方法和装置，即，对处于前缘和后缘处的机翼剩余部分的外壳的限制程度，直接与机翼包壳的刚度和内部结构相关。
结合附图的以下详细的实施例的介绍可使本发明这些和其他目的变得更易明了，其中附图是：
附图说明
图1是机翼组件示意剖面图，它包括贴敷到机翼内结构上的外包壳；
图2是根据本发明形成的装置的示意剖面图；
图3是图2装置顶视图。
最佳实施例
现参看附图，图1示出一典型直升机旋翼结构，它通常用数码2表示。旋翼有通常用数码4表示的内部结构，该内部结构包括：翼梁6，它是主要的支撑件，一般由金属或复合材料形成；蜂窝状芯零件8；和还可能有调谐重量、防冰系统等(细节未示出)，旋翼有玻璃纤维预浸处理外壳10，为了说明，在图中示出的外壳10是具有两层重叠玻璃纤维层组件12和14的双层包壳。旋翼2的前缘通常用数码16表示，后缘通常用18表示。
现参看附图2和3，图中示出将包壳10施加到旋翼2的内部构件4的本发明模制组件大体的示意图，该模制组件用数码20表示。模制组件20包括两个构件，一个是刚性模体22，最好是由钢制造的；另一个是均衡压力用覆盖板(caul plate)24，该板最好由预浸渍玻璃纤维层26叠合层制成。根据所希望的旋翼包壳外表面形状形成模体22和均衡压力覆盖板24的内表面28和30。很明显，旋翼玻璃纤维包壳片层施加到内部翼片构件上，将其包住，该组合的组件置位于模腔中。在均衡压力覆盖板上施加真空或正压力。应用粘合剂一般是可以提高温度进行固化。翼梁的位置用数码6表示，在剖视中用虚线示出。
均衡压力覆盖板24是由多层玻璃纤维或石墨预浸处理层26形成，包括：厚的前缘部分34，它覆盖旋翼组件2的前缘部16；较薄的后缘部36，覆盖旋翼后缘部18；和一中间部分38，其中，均衡压力覆盖板24的厚度由旋翼2的前缘部16到后缘部18逐渐减小。形成较厚和较薄均衡压力覆盖板24边缘部34和36的优选办法是逐渐减少通过均衡压力覆盖板中间部38的形成该板24的复合层26的数量。从而，例如形成均衡压力覆盖板部分34的复合层26是7层，则形成该板部分36的复合层26可以是3层。形成均衡压力覆盖板24每一部分的复合层的数目，如本文所指明的，是由旋翼2上玻璃纤维包壳10所要达到的刚度决定的。
均衡压力覆盖板各部34、38和36的边界是由下述确定的。在模腔32内的机翼梁6的位置决定着均衡压力覆盖板部分34、36和38的边界。翼梁6包封并限定与翼片2顺浆轴线相应的浆叶俯仰轴线44。通过俯仰轴线44和翼片2后端18并基本上将翼片的前缘部16平分的线46名为“弦线”。与弦线46垂直并通过俯仰轴线44延伸的线48，在均衡压力覆盖板24的外表面上限定均衡压力覆盖板24的厚边缘部34一端，并限定该板厚度逐渐减薄的中间部的38的开始点。与线48相平行与翼梁6的后边缘相切的线50确定出均衡压力覆盖板24的外表面上中间部38的端部，并确定薄的柔性均衡压力覆盖板部分36的开始点，均衡压力覆盖板部分36延伸到均衡压力覆盖板的后部边缘。均衡压力覆盖板24的部分34的表面30确定旋翼2前缘16的轮廓，通过使覆盖板24具有刚性基本硬固的部分34；便会使在均衡压力覆盖板部分34之下的外壳10的部分形成在旋翼2前缘部上比较精密的可很好地控制的预定形状。同时，通过使均衡压力覆盖板24具有能变形的柔性后缘部分36，在均衡压力覆盖板部分36之下的外壳10便可变形地贴到内部的后边缘翼片构件上，允许有尺寸变异同时沿翼片外壳后缘部分保持均匀的压力。如图3所示，由于均衡压力覆盖板24的部分34和36延伸在该板24的整个宽度W上，所以从翼片2的根端部到尖端部都存在这样的成形条件。这样形成的翼片会有从翼片的根到尖每边缘部分基本均匀的外壳。
易于明了，本发明的成形组件和方法会使机翼具有严密控制的前缘部形状，同时又允许在机翼后缘部分内部构件的尺寸变异。该机翼成形模制组件包括具有基本上刚性前缘部分和一柔性后缘部分的均衡压力覆盖板，当翼面成形时，该板提供了所希望的控制和挠性。这均衡压力覆盖板的刚性和柔性程度直接与在机翼上贴的外壳的所需刚度有关。
鉴于在不偏离本文介绍的发明情况下可以对已公开的实施例进行改变和变化，除了原附权利要求提出的之外，所述的本发明的公开内容不是为了限制本发明。

Claims (16)

1.一种将一外包壳层(10)贴敷到一机翼(2)的方法，该机翼有弦线(46)、俯仰轴线(44)、前缘部(16)和后缘部(18)，所述方法包括以下步骤：
装设模制组件(20)，所述组件包括刚性体件(22)和与所述刚性体件(22)配合的装置(24)，以便当外包壳层(10)贴敷到机翼(2)上时限定包封机翼(2)；
在模制组件(20)内安放机翼内构件(4)和外包壳层(10)；
在所述模制组件(20)的配合装置(24)上施加压力，以形成机翼(2)；
其特征在于是：
所述装设一模制组件的步骤包括装设具有刚性前缘部(34)和柔性后缘部(36)的一个均衡压力用覆盖板(24)，作为所述模制组件(20)的配合装置(24)；
施加在所述均衡压力用覆盖板(24)的所述刚性前缘部(34)的所述压力，使在机翼(2)前缘部(16)上的外包壳层(10)具有严格控制的弧线；
在所述均衡压力用覆盖板(24)的所述柔性后缘部(36)上施加的压力，使得即使机翼(2)内构件(4)尺寸有变异，也可使外包壳层(10)光滑地与机翼(2)的后缘部(18)一致。
2.根据权利要求1所述的方法，其特征在于：施加到所述均衡压力用覆盖板(24)的所述刚性前缘部(34)上的所述压力，被施加到限定在俯仰轴线(44)和弦线(46)之间的机翼(2)前缘部(16)区域内的外包壳层(10)上。
3.一种将外包壳层(10)贴敷到机翼(2)上的模制组件(20)，该机翼有弦线(46)、俯仰轴线(44)、前缘部(16)和后缘部(18)，所述模制组件包括：
刚性模体(22)，该模体具有限定机翼(2)一表面形状的内表面(28)；
与所述刚性模体(22)配合的装置(24)，用于当外包壳层(10)被贴敷到机翼(2)上时，限定机翼(2)，所述装置(24)有一限定机翼(2)外表面形状的内表面(30)；
其特征在于：
所述装置(24)是均衡压力用覆盖板，该均衡压力覆盖板具有，当所述包壳层(10)贴敷到机翼(2)上时，限定机翼(2)前缘部(16)一侧的刚性前缘部(34)和限定机翼(2)后缘部(18)一侧的柔性后缘部(36)。
4.根据权利要求3所述的模制组件(20)，其特征在于：所述均衡压力用覆盖板(24)的所述刚性前缘部(34)具有厚壁，所述均衡压力用覆盖板(24)的所述柔性后缘部(36)为薄壁。
5.根据权利要求4所述的模制组件(20)，其特征在于，所述均衡压力用覆盖板有一插入在所述刚性前缘部(34)和柔性后缘部(36)之间的中间部(38)，所述中间部(38)具有由所述刚性前缘部(34)向所述柔性后缘部(36)逐渐减小的壁厚。
6.根据权利要求5所述的模制组件(20)，其特征在于：机翼(2)内有内梁(6)，并且所述均衡压力用覆盖板(24)的所述刚性前缘部(34)位于在基本在该内梁(6)之上的机翼(2)的前缘部(16)上面。
7.根据权利要求6所述的模制组件(20)，其特征在于：机翼(2)有内部蜂窝芯(8)，并且所述均衡压力用覆盖板(24)的所述柔性后缘部(36)位于基本上是在该蜂窝芯(8)之上的机翼(2)的后缘部(18)上面。
8.根据权利要求3所述的模制组件(20)，其特征在于：所述均衡压力用覆盖板是由多层重叠的预浸渍复合材料(26)制成，在所述刚性前缘部(34)中的预浸渍复合材料(26)重叠层的层数比在所述柔性后缘部(36)中的预浸渍复合材料(21)重叠层的层数多。
9.根据权利要求3所述的模制组件(20)，其特征在于：所述均衡压力用覆盖板(24)的所述刚性前缘部(34)所具有的刚度至少是所述均衡压力用覆盖板的所述柔性后缘部(36)刚度的两倍。
10.根据权利要求9所述的模制组件(20)，其特征在于：所述均衡压力用覆盖板(24)的所述柔性后缘部(36)的刚度是被施加到机翼(2)上的外包壳层(10)的刚度的6倍。
11.一种用在将外包壳层(10)贴敷到机翼(2)上的模制组件(20)中的均衡压力用覆盖板(24)，该机翼(2)有弦线(46)、俯仰轴线(44)、前缘部(16)和后缘部(18)，所述均衡压力用覆盖板(24)包括：
多层预浸渍复合材料(26)的叠合层；
其特征在于：刚性前缘部(34)，当外包壳层(10)被施加到机翼(2)上时，它形成机翼(2)的前缘部(16)一侧轮廓；
和柔性后缘部(36)，该柔性后缘部(36)，当外包壳层(10)被施加到机翼(2)上时，限定出机翼(2)后缘部(18)一侧。
12.根据权利要求11所述的均衡压力用覆盖板(24)，其特征在于：所述均衡压力用覆盖板(24)的所述刚性前缘部(34)具有厚壁，所述均衡压力用覆盖板(24)的所述柔性后缘部(36)具有薄壁。
13.根据权利要求12所述的均衡压力用覆盖板(24)，其特征在于：所述均衡压力用覆盖板有连接所述刚性前缘部(34)和柔性后缘部(36)的中间部(38)，所述中间部(38)具有从所述刚性前缘部(34)向柔性后缘部(36)逐渐减小的壁厚。
14.根据权利要求12所述的均衡压力用覆盖板(24)，其特征在于：在所述刚性前缘部(34)中的预浸渍复合材料(26)的叠合层数比在所述柔性后缘部(36)中的预浸渍复合材料层数大。
15.根据权利要求11所述的均衡压力用覆盖板(24)，其特征在于：所述均衡压力用覆盖板(24)的所述刚性前缘部(34)的刚度至少是所述均衡压力用覆盖板(24)所述柔性后缘部(36)刚度的两倍。
16.根据权利要求15所述的均衡压力用覆盖(24)，其特征在于：所述均衡压力用覆盖板(24)的所述柔性后缘部(36)的刚度是被贴敷到机翼(2)上的外包壳层(10)的6倍。
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