CN102378676B - 在两个区域之间具有楔形部的复合材料零件 - Google Patents

在两个区域之间具有楔形部的复合材料零件 Download PDF

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CN102378676B
CN102378676B CN201080015082.7A CN201080015082A CN102378676B CN 102378676 B CN102378676 B CN 102378676B CN 201080015082 A CN201080015082 A CN 201080015082A CN 102378676 B CN102378676 B CN 102378676B
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约瑟·路易斯·洛萨诺卡西亚
约瑟·奥伦西奥·格拉纳多马卡里利亚
文森特·马丁内斯巴尔德格拉马
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    • 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
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
    • B29C70/86—Incorporated in coherent impregnated reinforcing layers, e.g. by winding
    • B29C70/865—Incorporated in coherent impregnated reinforcing layers, e.g. by winding completely encapsulated
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
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    • B32B3/08—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by features of form at particular places, e.g. in edge regions characterised by added members at particular parts
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
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    • B32B5/26—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer another layer next to it also being fibrous or filamentary
    • 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
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • 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
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • 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
    • B29C70/38—Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
    • B29C70/386—Automated tape laying [ATL]
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2031/00—Other particular articles
    • B29L2031/772—Articles characterised by their shape and not otherwise provided for
    • B29L2031/7738—Wedge shaped
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2605/00—Vehicles
    • B32B2605/18—Aircraft
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    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T156/00—Adhesive bonding and miscellaneous chemical manufacture
    • Y10T156/10—Methods of surface bonding and/or assembly therefor
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T156/00—Adhesive bonding and miscellaneous chemical manufacture
    • Y10T156/10—Methods of surface bonding and/or assembly therefor
    • Y10T156/1052—Methods of surface bonding and/or assembly therefor with cutting, punching, tearing or severing
    • Y10T156/1062—Prior to assembly
    • Y10T156/1075—Prior to assembly of plural laminae from single stock and assembling to each other or to additional lamina
    • 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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    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
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    • Y10T428/12486—Laterally noncoextensive components [e.g., embedded, etc.]
    • 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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Abstract

本发明涉及一种复合材料零件(5)，在两个区域(11，15)之间具有斜道(13)，第二区域(15)比第一区域(11)短，该复合材料零件的结构从其外表面(21)至其内表面(23)包括：第一部分(31)，由平行于其外表面(21)延伸的至少两个连续织物(41)形成，斜道(13)的坡度在20％和50％之间；三角柱形状的楔形部(33)，其较大表面(27)的尺寸形成为形成具有小于20％的坡道；第二部分(35)，由平行于由具有所述楔形部(33)放置其上的所述第一部分(31)限定的表面延伸的多个连续织物(45)形成。本发明还涉及用于生产该零件(5)的方法。

Description

在两个区域之间具有楔形部的复合材料零件
技术领域
本发明涉及一种在两个区域之间具有楔形部的复合材料零件的铺设结构，其通过在高压釜中固化所述铺设结构而制造，并且更特别地，涉及用于飞机结构的复合材料零件的铺设结构。
背景技术
用于基本上包括使用ATL“自动带铺设”铺设薄片的第一阶段和在高压釜中固化的第二阶段的部件制造过程在航空业中是众所周知的。
在铺设(lay-up)步骤中，诸如预浸料坯(其为纤维加固件和聚合物基质(matrix)的可储存混合物)之类的复合材料层放置在合适形状的模具/工具中。
这个材料可以是各种形式，特别是薄片形式。在热硬化基质的情况下，通过另一个过程，树脂通常部分地固化或产生受控粘度，熟知为B阶段。
复合材料的薄片不是随机地定位，而是以一定数量定位在每个区域中，并且具有它们的纤维加固件(典型地为碳纤维)的定位，这是根据在每个区域中零件必须承受的作用力的性质和大小来确定的。ATL(“自动带铺设”)机通常用于此。
假设用于这种机器的允许坡度小，自动带铺设机(Automatic tapelay-up machines)用于制造平的或大致平的铺设是非常有效的。
然而，存在包括楔形部的飞机结构，虽然从设计的角度来看，楔形部期望应该具有比ATL机所允许使用的坡度更大的坡度，但为了遵守这些机器的加工限制，楔形部最终设计为具有较小坡度。这就产生了本发明意图克服的各种缺点。
发明内容
本发明的一个目的在于提供一种由复合材料制成的零件的铺设结构，其配置包括在两个区域之间的楔形部，并且其可以使用ATL机制造，即使楔形部的坡度大于使用这种类型机器要求的坡度。
本发明的另一个目的在于提供一种用于由复合材料制成的零件的铺设结构，其配置包括在两个区域之间的楔形部，并且其可以使用ATL机更容易制造，而没有涉及重量增加的楔形部的配置的改变。
本发明的另一个目的在于提供一种用于由复合材料制成的零件的铺设结构，其配置包括在两个区域之间的楔形部，该楔形部使得更容易ATL机进行制造，而没有改变在零件和额外元件之间提供连接的楔形部的配置。
这些和其他目的的第一个方面通过从复合材料薄片层的铺设来制造的零件实现，该零件包括在第一区域和一般比第一区域短的第二区域之间的楔形部，该零件的结构从其外表面至其内表面包括：
第一部分，由平行于零件的外表面延伸的至少两个连续薄片(41)形成，楔形部的外表面的坡度在20％和50％之间，
三角柱，放置在所述第一部分上，三角柱的较大表面以如下方式定尺寸：该较大表面形成具有小于20％的坡度并且在所述第二区域的开始处结束的楔形部，
第二部分，由多个连续薄片形成，所述多个连续薄片平行于由所述第一部分与放置在所述第一部分上的三角柱33限定的表面延伸。
在本发明的优选实施例中，楔形部的外表面的坡度在20％和50％之间，三角柱的最大表面的坡度小于15％。通过这种方式，可以实现可以用于设计有楔形部的飞机结构的复合材料的大多数零件的铺设结构。
在本发明的另一个优选实施例中，三角柱由在与零件相同的周期中固化的复合材料制成。通过这种方式促进生产。
在第二方面中，提供一种用于制造提到的零件的方法，该方法包括将复合材料薄片铺设在具有该零件的外表面形状的铺设工具上，并且在合适的设备中通过下述阶段固化复合材料薄片：
在第一阶段中，使用ATL机铺设第一部分的薄片并手动压紧铺设的第一部分的薄片，
在第二阶段中，定位三角柱，
在第三阶段中，使用ATL机来铺设和压紧第二部分的薄片。
根据本发明的目标的说明性实施方式的接下来联系附图的详细描述，本发明的其他特征和优势将是明显的。
附图说明
图1是在两个区域之间具有楔形部的复合材料的零件的横截面的图解视图，图1的上部说明从设计的角度来看可取的结构，图1的下部说明在铺设该零件的过程中用来适应使用ATL机器所必需的限制的结构。
图2是图1中的具有一些加强元件的相同零件的横截面的图解视图，其用于说明在已知技术中采用结合楔形部的零件引起的问题之一。
图3a是具有抗扭箱的飞机的水平尾翼的视图，其中衬里是在两个区域之间具有楔形部的部分，以及图3b是机翼后缘的部件的连接区域的局部详细视图。
图4是根据本发明的在两个区域之间具有楔形部的零件的结构的横截面图解视图。
图5a、5b及5c是图解根据本发明的铺设具有位于两个区域之间的楔形部的零件的过程的视图。
具体实施方式
本发明涉及由复合材料制造的具有楔状的零件，在图1和2中图示的零件3、3’在两个区域11、15之间具有楔形部l3。这些附图也显示厚度比零件3、3’小的零件7，零件7必须在区域15中连接到它们，零件7的外表面与区域11的外表面成一直线。
作为在航空业中这种类型的零件的示例，可能会提及图3a和3b中图示的尾翼的抗扭箱的衬里，其中零件3、3’中的区域11对应于抗扭箱的衬里5，区域15对应于机翼前缘和机翼后缘的部件9的连接边缘7，连接边缘7又对应于零件7。楔形部13、13’由零件7和零件3、3’之间的厚度差异确定，以使零件3、3’的区域11的外表面和零件7的外表面具有适当的空气动力学连续性。
图1和2中的零件3、3’分别地显示从设计的角度是可取的结构和使用已知技术可以制造的结构。
在图1所示的情况中将会看到，由零件3’引起的一个问题是对应于阴影区域19的重量增加，零件3’的结构包括部分13’，部分13’比零件3中的楔形部13更平缓地成楔形或比零件3中的楔形部13的斜度小，楔形部13具有较大坡度。
在如图2所示的情况中将会看到，除了与在前面情况中相同的重量增加问题以外，由零件3’引起的一个问题在于，区域15的最终部分的位置与连接到零件7的T形的加强部件17冲突，零件3’的结构包括部分13’，部分13’具有比零件3中的楔形部13平缓的坡度，楔形部13具有较大坡度，并且问题在于，楔形部朝向零件3’的区域15延伸使得难以将加工板或该装配到其内表面，因为难以在倾斜表面上做到这一点。
因此如上所述，为了避免上述缺点，期望能够生产具有楔形部的复合材料零件，楔形部在其外表面上具有比ATL加工所需要的坡度更大的坡度。
根据本发明，通过在两个区域11、15之间具有楔形部13的零件5克服这个问题，其中取决于设计要求，楔形部13的外表面25的坡度在20％和50％之间，并且如在图4中显示，该零件结构包括：
第一部分31，由平行于零件5的外表面21延伸的数量减少的薄片形成，
三角柱33，放置在所述第一部分31上，三角柱33的最大表面27形成具有少于20％坡度并且在零件5的第二区域15的开始处结束的楔形部，
由多个连续薄片形成的第二零件35，所述多个连续薄片平行于由第一部分31与放置在第一部分上的三角柱33限定的表面延伸。
如可以在图4中看出，三角柱33的两个较小表面限定平行零件5的外表面21的分段表面的分段表面，三角柱33的较大表面27具有与铺设机的需要一致的坡度，为了铺设机应正确地操作。因此，其功能是将三角柱33的表面25的非常大的倾斜坡度转换成三角柱33的表面27的小坡度，以协助使用ATL机铺设用于第二部分35的薄片。除此以外将可见，零件5的内表面23是用于安装必须支撑在其上的部件的最佳表面。
优选地，三角柱33优选地使用在与零件相同周期中固化的碳纤维的粗纱制造。在其他实施例中，三角柱33例如可以由诸如玻璃纤维的材料制成。
在本发明的另一个优选实施例中，三角柱33的最大表面的坡度小于15％。
通过随后的附图5a、5b、5c将可见在零件5的铺设中彼此跟随的三个基本阶段：
-在第一阶段中，部分31的薄片41与零件5和铺设的楔形部39的外部几何形状一致。可以使用ATL机铺设所述薄片，但是必须手动压紧所述薄片，因为考虑到楔形部的坡度，该机器无法正确地做到这一点，
-在第二阶段中，安装三角柱33。三角柱33在零件5上的位置避免了如果它位于部件5的外侧将产生的表面光洁度和开裂的问题，
-在第三阶段中，使用ATL机以正常方式铺设部分35的薄片45。
包括在由随后权利要求限定的范围内的这些修改可以引入刚刚描述的优选实施例。

Claims (5)

1.一种通过铺设复合材料薄片制造的零件(5)，该零件包括在第一区域(11)和第二区域(15)之间的楔形部(13)，其特征在于，该零件的结构从其外表面(21)至其内表面(23)包括：
第一部分(31)，由平行于零件(5)的外表面(21)延伸的至少两个连续薄片(41)形成，楔形部(13)的外表面包括倾斜表面(25)，倾斜表面(25)的坡度在20％和50％之间，
三角柱(33)，放置在所述第一部分(31)上，三角柱的较大表面(27)以如下方式定尺寸：该较大表面形成具有小于20％的坡度并且在所述第二区域(15)的开始处结束的楔形部，并且具有两个较小表面，所述两个较小表面限定平行于零件(5)的外表面(21)的分段表面的分段表面，
第二部分(35)，由多个连续薄片(45)形成，所述多个连续薄片(45)平行于由所述第一部分(31)与放置在所述第一部分(31)上的所述三角柱(33)限定的表面延伸。
2.根据权利要求1所述的零件(5)，其特征在于，三角柱(33)的较大表面(27)的坡度小于15％。
3.根据权利要求1或2所述的零件(5)，其特征在于，所述三角柱(33)由在与零件(5)相同的周期中固化的复合材料制成。
4.根据权利要求1或2所述的零件(5)，其特征在于，零件(5)形成飞机横尾翼的抗扭箱的衬里的一部分。
5.一种用于生产根据权利要求1至4中任何一项的零件(5)的方法，该方法包括将复合材料薄片铺设在具有零件(5)的外表面形状的铺设工具(39)上，并且在合适的设备中固化铺设的复合材料薄片，其特征在于：
a)在第一阶段中，使用ATL机铺设第一部分(31)的薄片(41)，并手动压紧铺设的第一部分(31)的薄片(41)，
b)在第二阶段中，安装三角柱(33)，
c)在第三阶段中，使用ATL机来铺设和压紧第二部分(35)的薄片(45)。
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