CN1159782A - 翼型结构的成型方法和装置 - Google Patents

翼型结构的成型方法和装置 Download PDF

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CN1159782A
CN1159782A CN95195368A CN95195368A CN1159782A CN 1159782 A CN1159782 A CN 1159782A CN 95195368 A CN95195368 A CN 95195368A CN 95195368 A CN95195368 A CN 95195368A CN 1159782 A CN1159782 A CN 1159782A
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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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Raytheon Technologies Corp
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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。钢模用在轮廓最严格的机翼部位，这往往是上翼面。
在形成象直升飞机构件这样的复合材料产品的最新进展，介绍了各种形状结构模制组件的应用，这些模制组件包括一般由钢制成的刚性模件和相配的柔性的均衡压力用覆盖板件，以便改进模制操作。1991，12，10授与A.C.Dublinski等的美国专利5,071,338，1992，2，11授与R.J.Sjmkulak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均介绍用具有刚性模件和互补的柔性均衡压力用覆盖板件的模制组件形成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是被建议用于成形被制造产品的复杂的细节部分(专利5,071,338)；并也用于改善模制产品固化后从该模制产品上将模制构件剥除的容易程度(专利5,152,949)。上述每一专利中介绍的模制产品均是飞机构件。
发明内容
本发明涉及使用模制组件组装飞机等如直升飞机的旋翼的机翼外包壳和机翼的内部结构构件。本发明的模制组件包括一刚性模体，该模体最好是钢制的，具有限定机翼上表面形状的空腔。模制组件还包括一互补的均衡压力用覆盖板，它有一限定机翼下表面形状的内空腔。均衡压力用覆盖板具有在该板全长上基本是刚性的前缘部，和一基本上是柔性的相对的后缘部。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与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。
鉴于不偏离本发明的精神可对本公开的实施例加以变化和修改，故除后附的权利要求外，不构成对本发明的限制。

Claims (16)

1.一种将外包壳贴敷到机翼上的方法，该机翼具有弦线、俯仰轴线、前缘部和后缘部，上述方法包括以下步骤：
a)向机翼前缘部的所述包壳层施加一均匀的基本刚性的压力，使在该机翼前缘部上的所述包壳具有高度控制的弦线；
b)同时向机翼后缘部的所述包壳层施加一均匀柔性压力，使得沿机翼的后缘的包壳上形成均匀压力，即使机翼内构件尺寸变异，也可操纵此压力使得所述包壳层与所述后缘部分一致。
2.根据权利要求1所述的方法，其中，所述刚性压力被施加到机翼一区域所述包壳层上，该区域位于通过俯仰轴线并与所述弦线垂直的直线一侧的前缘部。
3.一种将外包壳层贴敷到机翼上的模制组件，该翼面有弦线、俯仰轴线、前缘部和后缘部，所述模制组件包括：
a)模具主体，该主体有限定该机翼表面轮廓的空腔；
b)均衡压力覆盖板，所述覆盖板与所述模具主体配合，当该包壳层贴到该翼面上时限制该翼型，所述均衡压力覆盖板具有一确定该机翼相对表面轮廓的空腔，还具有刚性前缘部和柔性后缘部，当所述包壳层贴到该翼上时，所述刚性前边缘部确定出该机翼前缘部一侧，所述柔性后缘部确定出该机翼后缘一侧。
4.根据权利要求3所述的模制组件，其中，所述均衡压力覆盖板的所述刚性前边缘部具有一厚壁，所述均衡压力覆盖板的柔性后缘部有一薄壁。
5.根据权利要求4所述的模制组件，其中，所述均衡压力覆盖板有一插入在所述刚性前缘部和柔性后缘部之间的中间部分，所述中间部分具有厚度逐渐由所述刚性前缘部向柔性后缘部减薄的壁。
6.根据权利要求5所述的模制组件，其中，所述均衡压力覆盖板的刚性前缘部分基本位于该翼梁之上的机翼前缘部上。
7.根据权利要求6所述的模制组件，其中，该机翼有内梁，并且所述均衡压力覆盖板的所述柔性边缘部基本上位于蜂窝芯部之上的机翼后缘部上。
8.根据权利要求3所述的模制组件，其中，所述均衡压力用覆盖板由多个叠加的预浸渍复合材料层制成，并且其中，叠加的复合材料层数在所述刚性前缘部中比在所述柔性后缘中的多。
9.根据权利要求3所述的模制组件，其中，所述均衡压力用覆盖板的刚性前缘部具有的刚度至少是该板柔性后缘部的刚度的两倍。
10.根据权利要求9所述的模制组件，其中，所述均衡压力用覆盖板柔性后缘部具有的刚度，是被贴敷到机翼上外包壳层刚度的6倍。
11.一种用于将外包壳层贴敷到机翼的模制组件中用的均衡压力用覆盖板，该机翼具有弦线、俯仰轴线、前缘部和后缘部，所述均衡压力用覆盖板包括刚性前缘部，当把包壳层贴到机翼上时，形成所述刚性前缘部使机翼前缘部一侧轮廓，所述均衡压力用覆盖板还包括柔性后缘部，当所述包壳层被施加到机翼上时，所述柔性后缘部确定出机翼后缘部一侧。
12.根据权利要求11所述的均衡压力用覆盖板，其中，所述刚性前部具有一厚壁，所述柔性后缘部具有一薄壁。
13.根据权利要求12所述的均衡压力用覆盖板，进一步包括连接所述刚性前缘部和柔性后缘部的中间部分，所述中间部分具有由所述刚性前缘部向柔性后缘部逐渐减薄的壁。
14.根据权利要求12所述的均衡压力用覆盖板，其中，所述的均衡压力用覆盖板是由预浸渍复合材料的多层叠合层形成，其中，在所述刚性前缘部中复合材料叠层的层数比所述柔性后缘部中复合材料叠层的层数多。
15.根据权利要求11所述的均衡压力用覆盖板，其中，所述刚性前缘部具有的刚度至少是所述柔性后缘部刚度的两倍。
16.根据权利要求15所述的均衡压力用覆盖板，其中，所述柔性后缘部具有的刚度是被贴敷到机翼上外包壳刚度的6倍。
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