CN104023954B - 具有共结合的加强件的复合材料柱状结构及制造方法 - Google Patents
具有共结合的加强件的复合材料柱状结构及制造方法 Download PDFInfo
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Abstract
一种柱状结构包含大致中空的层压板芯(34)、外复合材料蒙皮(42)和套筒状加强件(36)。例如由金属或陶瓷形成的加强件(36)围绕层压板芯(34),并且被夹在芯与外蒙皮(42)之间,用于抵抗强加在柱状结构上的压缩载荷。
Description
技术领域
本公开大体涉及复合材料柱状结构,并且更具体涉及内在地增强以更好地抵抗轴向压缩载荷的混合复合材料管状支柱。
背景技术
由于其良好的力重量比,由复合材料形成的柱状结构在各种各样的应用中使用。例如,复合材料管状支柱可以在航天工业中被用作在沿支柱的纵向轴线的任一方向上传递载荷的支撑或撑杆,因此使支柱处于压缩或拉伸。支柱端部上的配合件在支柱与结构的连接位置处提供附加强度。
上面提到的管状支柱可以由纤维加强的树脂层压板制造。当处于拉伸时,这类层压板可以表现出比处于压缩时更大的承载能力。这是因为树脂的耐压强度通常小于其抗拉强度。因此,为了满足性能指标,必须加大支柱的尺寸,以承受指定水平的压缩载荷。然而,加大支柱的尺寸会增加成本,和/或将不期望的重量增加给交通工具或支柱连接的其他结构。
因此,存在对表现出改善的承受压缩载荷能力的复合材料柱状结构的需要。还存在对制造具有几乎很少或不向结构增加重量的改善的压缩载荷承受能力的柱状结构的低成本方法的需要。
发明内容
所公开的实施例提供了一种复合材料柱状结构,诸如管状支柱,其表现出改善的抵抗轴向压缩载荷的能力,同时几乎很少或不向结构增加重量。通过包含围绕形成支柱的芯的套筒状层压的层板的加强件来实现改善的压缩载荷容量。加强件允许“适当尺寸的(right-sized)”复合材料管状支柱以及类似的柱状结构被设计为满足承受压缩以及拉伸载荷的承载指标,同时最小化支柱的重量。
根据一个所公开的实施例,提供了一种柱状结构,其包含大致中空的层压板芯、外复合材料蒙皮和加强件。加强件围绕层压板芯,并且被夹在层压板芯与外蒙皮之间,用于抵抗强加在柱状结构上的压缩载荷。层压板芯可以是大体管状的,并且加强件可以包括大体上完全围绕层压板芯延伸的材料层。材料层可以是诸如但不限于钛的金属、预固化的纤维加强的复合材料或陶瓷中的一个,而层压板芯可以是纤维加强的树脂,诸如碳纤维加强的塑料。加强件可以包含沿平行于层压板芯的轴线的方向接合在一起的第一半部和第二半部。在一个实施例中,加强件可以包括在其内壁上的波纹,该波纹可以在层压板的固结与固化期间控制芯的下层层压的层板的起皱。
根据另一实施例,支柱包含大致管状的纤维加强的树脂芯和围绕芯的套筒状加强件,其中套筒状加强件具有比树脂的耐压强度更大的耐压强度。套筒状加强件可以是波纹状金属,并且可以包括沿在管状芯的纵向方向上延伸的缝组装在一起的第一半部和第二半部。支柱还可以包含一对间隔开的端部配合件,其包括适合于将支柱连接至结构的一对连接销。销大体位于第一平面中,而缝大体位于大致垂直于第一平面的第二平面中。在一种变体中,套筒状加强件是陶瓷。在另一变体中,套筒状加强件是钛,而纤维加强的树脂芯是碳纤维加强的塑料。套筒状加强件与芯共结合,并且与外蒙皮共结合。
根据另一实施例,提供了一种制造支柱的方法,其包含:制造复合材料层压板芯,制造套筒状加强件,在芯上面组装加强件,以及在套筒状加强件上面制造外蒙皮。该方法还可以包含,使套筒状加强件与芯共结合,并且与外蒙皮共结合。制造套筒状加强件可包括在金属构件的内侧表面上形成波纹。制造复合材料层压板芯包括,铺设纤维加强的树脂的层板,而在芯上面组装套筒状加强件包括,在波纹抵靠芯的铺设的层板的情况下将金属构件放在芯上。该方法还可以包含,固结并固化芯,以及在固结期间利用金属构件上的波纹来控制层板的起皱。
根据本发明的另一方面,提供了一种柱状结构,其包含大致中空的层压板芯、外复合材料蒙皮和加强件,其中加强件围绕层压板芯,并且被夹在芯与外蒙皮之间,用于至少抵抗强加在柱状结构上的压缩载荷。有利地,层压板芯是大体管状的,并且加强件包括大体上完全围绕层压板芯延伸的材料层。有利地,材料层是金属和陶瓷中的一个,而层压板芯是纤维加强的树脂。有利地,材料层是钛,而层压板芯是碳纤维加强的塑料。有利地,加强件可以是具有大体上沿纵向层压板芯的轴线接合的第一半部和第二半部的金属。有利地,加强件可以包括具有与芯接触的波纹并沿芯的纵向方向延伸的套筒状材料层。
根据本发明的另一方面,提供了一种支柱,其包含大致管状的纤维加强的树脂芯和围绕芯的套筒状加强件,其中套筒状加强件具有比树脂的耐压强度更大的耐压强度。有利地,套筒状加强件可以是金属。有利地,套筒状加强件可以是波纹状的。有利地,套筒状加强件可以包括沿在芯的纵向方向上延伸的缝组装在一起的第一半部和第二半部。有利地,缝被布置在围绕芯的显著优化管状体的抗弯强度的位置处。有利地,支柱还可以包含一对间隔开的端部配合件,其包含包括大体上位于第一平面中并且适合于将支柱连接至结构的一对连接销,并且其中缝中的至少一个大体上位于大致垂直于第一平面的第二平面中。有利地,套筒状加强件是陶瓷。有利地,套筒状加强件是钛,并且具有在其上带有凸起的带状物的内侧表面,而纤维加强的树脂芯是碳纤维加强的塑料。有利地,套筒状加强件包括均具有内侧表面的第一半部和第二半部,其中内侧表面提供有与芯接触的脊。有利地,支柱还可以包含覆盖套筒状加强件的外蒙皮,并且其中套筒状加强件与芯共结合,并且与外蒙皮共结合。
根据本发明的另一方面,提供了一种制造支柱的方法,其包含:制造复合材料层压板芯,制造套筒状加强件,在芯上面组装加强件,以及在套筒状加强件上面制造外蒙皮。有利地,该方法还可以包含,使套筒状加强件与芯共结合,并且与外蒙皮共结合。有利地,步骤制造套筒状加强件包括在构件的内侧表面上形成波纹,制造复合材料层压板芯包括铺设纤维加强的树脂的层板,而在芯上面组装套筒状加强件包括在波纹抵靠芯的铺设的层板的情况下将构件放在芯上。有利地,该方法还可以包含,固结并固化芯,以及在固结期间利用金属构件上的波纹来控制层板的起皱。有利地,在心轴上铺设层板,并且该方法还包含在执行固化与固结之后移除芯。有利地,制造套筒状加强件的步骤包括,制造第一半部和第二半部。有利地,在芯上面组装套筒状加强件的步骤,包括将半部放在芯上面,并沿芯的纵向方向上布置在半部之间的缝。有利地,该方法还可以包含,在芯的固结与固化期间利用套筒状加强件来控制芯的起皱。
所述特征和功能可以在本公开的各种实施例中独立地实现,或可以在其它实施例中组合,其中参考下面的说明和附图可看出其进一步的细节。
附图说明
说明性实施例的被确信为新颖性特征的特性在所附权利要求中阐述。然而,当结合附图阅读时,说明性实施例以及优选的使用方式、进一步的目的及其特征将通过参考本公开的说明性实施例的下面的具体实施方式而被最好地理解,其中:
图1是根据一个所公开的实施例的表现出改善的抵抗轴向压缩载荷的能力的混合复合材料管状支柱的立体图的图示说明。
图2是沿图1中的线2-2截取的剖视图的图示说明。
图3是图1所示的处于制造的中间状态的支柱的立体图的图示说明,其中正在层压板芯上安装加强件的两个半部。
图4是类似于图3但示出了已经被安装的加强件的两个半部的图示说明。
图5是类似于图4但示出了具有波纹的加强件的替代实施例的图示说明。
图6是在图5中6-6所示区域中的波纹状加强件的立体图的图示说明。
图7是在图2中被指定为图7的区域但图示说明了波纹状形式的加强件的使用的图示说明。
图8是另一形式的加强件的剖视图的图示说明。
图9是制造根据所公开的实施例的混合复合材料柱状结构的方法的流程图的图示说明。
图10是飞机制造与保养方法的流程图的图示说明。
图11是飞机的方框图的图示说明。
具体实施方式
首先参照图1,被示为细长支柱20的复合材料柱状结构包括大致圆柱形的管状体22和用于将支柱20连接至结构(未示出)的一对端部配合件24。支柱20可以用于沿管状体22的纵向轴线25传递压缩载荷,并且还可以传递使管状体22处于拉伸的载荷。每个端部配合件24可以由金属(诸如铝或钛)、或复合材料或其他合适的材料制成。可以通过铸造、机加工或其他常用的制造技术制造端部配合件24。在端部配合件24由复合材料形成的应用中,它们可以包括金属插入件和/或金属套管(未示出)。
每个端部配合件24可以包括U形夹26,U形夹26具有沿轴线32对齐的中心开口28,用于接收将支柱20附接至结构的U形夹销30。U形夹销30的轴线32大体上位于相同的平面35中。U形夹销30连同U形夹26一起形成支柱20与其所附接的结构之间的枢转连接。支柱20可以被用作例如但不限于飞机发动机(未示出)与机身(未示出)之间的撑杆。取决于支柱20的特定用途,各种其他类型端部配合件24中的任何一种都是可能的。同样,如上所述,支柱20可以用于沿支柱20的纵向轴线25双轴向地传递载荷,因此可以沿纵向轴线25使支柱20处于拉伸或压缩,或者可以沿纵向轴线25以交替的方式使支柱20处于拉伸与压缩。在一些应用中,支柱20还可能遭受有限的扭转载荷。在所示的示例中,管状体22的横截面形状是大体圆的,并且沿其长度是恒定的,然而其他横截面形状是可能的,诸如但不限于,正方形、三角形、六边形或五边形形状。同样,管状体22可以沿其长度具有一个或更多个锥度。
现在参照图2,管状体22大致包含夹在圆柱形芯34与外蒙皮38之间的大致圆柱形的套筒状加强件36。套筒状加强件36增加了管状体22的耐压强度。芯34可以包含多个合适纤维加强的树脂的层板48(图7),合适纤维加强的树脂诸如但不限于可以通过手动或传统的自动铺设技术铺设在可移除的心轴(未示出)上面的碳纤维加强的塑料(CFRP)。外蒙皮38在套筒状加强件36上面形成防护层,并且还可以包含多个层压的纤维加强的树脂的层板。外蒙皮38的层板还将套筒状加强件36保持在适当为位置,并且可以使加强件36能更好地抵抗压缩载荷。
在一个实施例中,套筒状加强件36是圆柱形形状,并且可以包含材料层42,该层42被形成为大体延伸管状体22的整个长度的半圆形的第一加强件半部36a和第二加强件半部36b。在其他实施例中,材料层42可以包含单个构件或多于两个构件。层42可以包含表现出期望程度的耐压强度(诸如金属箔或陶瓷)并且与形成芯34的材料兼容的合适材料。例如,在芯34由CFRP形成的情况下,形成加强件36的材料层42可以包含钛。层42还可以包含含有单向加强纤维的预塑化树脂,单向加强纤维诸如但不限于抵抗作用于支柱20的轴向压缩载荷的钢纤维。套筒状加强件36的耐压强度大于形成芯34的树脂的耐压强度,以便增加支柱20的整体耐压强度。
在所示的示例中,采用两件式加强件36(半部36a、36b)可以被预先形成,然后围绕芯34进行组装,从而形成直径上对置的结合线或缝44。加强件半部36a、36b可以沿或不沿缝44机械地接合。在一个实施例中,尽管未在附图中示出,两个半部36a、36b可以其他沿缝44相互重叠,以便允许半部36a、36b相对于彼此滑动,并且当下层芯34在芯34的固结与固化期间收缩时稍微塌陷。取决于希望增加给支柱20的耐压强度的量,材料层42的厚度“T”可以随着应用而变化。尽管在所示的示例中仅示出了一个圆柱形加强件36,但支柱20可以包括嵌入在管状体22中的多个轴向同心的加强件36(未示出)。在其他实施例中,加强件36和/或芯34可以沿管状体22的长度从薄横截面部分到更厚的横截面部分逐渐变细,而管状体22的外圆柱形形状大体上保持恒定。
参照图3,可以通过在端部配合件24上面铺设芯34的层板48(图7)而组装支柱20,然而将端部配合件24附接至芯34的其他方法是可能的。套筒状加强件36的两个半部36a、36b可以通过合适工艺预先形成,然后在芯34上面进行组装。取决于加强件36的厚度“T”(图2),可以通过将芯34用作心轴而在芯34上面形成材料层42而使加强件36形成形状。图4图示说明了已经被组装在芯34上面的两个半部36a、36b,并且描述了如上所述的可以表示两个半部36a、36b的机械接合线连接的缝44中的一个。可以选择缝44的周向位置,以便优化管状体22的抗弯强度。例如,在所示的实施例中,可以周向地布置缝44,以便它们位于大体垂直于U形夹销30的平面35的平面37(图1和2)中或附近。使缝44以这样的方式大致垂直于销30的轴线定向可以使加强件36能更好地抵抗靠近或大体平行于平面35的平面中或者平面35内的弯矩,并且由此提高支柱20的抗弯强度。然而,应当注意,即使当缝44不被布置在优化支柱20的抗弯强度的周向位置处时,也可以实现所公开的实施例提供的益处。
图5图示说明了支柱20的替代实施例,其包括具有波纹46的两件式套筒状圆柱形加强件36。参照图6,波纹46包括加强件36的内侧表面45上的周向间隔开的、纵向延伸的波纹脊46a。可以通过适合于制成加强件36的材料的多种工艺的任一种形成波纹46。参照图7,可以看出,波纹46的脊46a向下延伸到芯34的层压的层板48内,并且抵靠芯34的层压的层板48被压紧。在支柱20的固结与固化期间,芯收缩,而波纹脊46a抵靠芯34被压紧,趋向于控制芯30的层板48中的褶皱形成。由于波纹脊46a在脊46a附近压下并延长层板48的一些部分,以便在固结/固化期间绷紧和/或吸收层板48的收缩,因此实现这种皱褶控制。
可以利用其他形式的加强件36实现套筒状加强件36在固结工艺期间控制下层层板48起皱的能力。例如,参照图8,代替包含上述加强件36的波纹状材料层42,可以在材料层42已经被形成为期望的形状之前或之后通过合适的技术将纵向延伸的、间隔开的任何合适材料的凸起带状物47作用于材料层42的内侧表面45。
注意力指向图9,其图示说明了制造上述复合材料管状支柱20的方法的全部步骤。在50处开始,通过在合适的心轴(未示出)上面铺设复合材料层板48来制造层压的芯30,心轴例如可以是可充气的或易融化的心轴。其次,在52处,可以通过将一个或更多个材料层42预先形成为期望横截面形状的半部36a、36b、或通过将芯30用作心轴而在芯30上面形成材料,制造加强件36。在步骤54处,在芯30上面应用合适的粘合剂,其后在56处,在芯30上面组装加强件36。加强件半部36a、36b之间的缝44可以被布置为使得它们大体位于大体垂直于U形夹销30轴线32的平面35的平面37中,以便抵抗弯曲力,然而,取决于端部配合件24的结构与几何形状,缝44可以被布置在其他位置处。在步骤58处,在加强件36上面应用合适的粘合剂。在步骤60处,通过在加强件36上面铺设另外的复合材料层板而使外蒙皮38应用在加强件36上面。在步骤62处,支柱20被压实、压紧以及固化,由此使加强件36与芯30和外蒙皮38共结合。最后,在步骤64处,可以移除在其上铺设芯30的心轴。
本公开的实施例可以应用于各种潜在应用,尤其是应用于运输行业中,包括例如航空航天、船舶、汽车应用以及可以使用自动铺设设备的其他应用。因此,现在参照图10和11,本公开的实施例可以用于在图10中示出的飞机制造与保养方法70以及在图11中示出的飞机72的情形中。仅举几例,所公开的实施例的飞机应用可以包括例如但不限于载荷传递构件,诸如,支柱、支撑、连接杆以及类似的柱状结构。在试制期间,示例性方法70可以包括飞机72的规格与设计74以及材料采购76。在生产期间,进行飞机72的组件与部件制造78以及系统整合80。其后,飞机72可以通过认证与交付82,以便使其服役84。在由客户使用时,飞机72被安排进行日常的维护与保养86(其还可以包括更改、重新配置、翻新等)。
可以由系统集成商、第三方和/或操作者(例如,客户)执行或实施方法70的每个过程。为了该描述的目的,系统集成商可以包括但不限于任意数量的飞机制造商和主系统转包商;第三方可以包括但不限于任意数量的售卖者、转包商和供应商;而操作者可以是航空公司、租赁公司、军事实体、服务机构等。
如在图11中示出的,通过示例性方法70生产的飞机72可以包括机身88以及复数个系统90和内部92。高级系统90的示例包括一个或更多个推进系统94、电气系统96、液压系统98和环境系统100。可以包括任意数量的其它系统。尽管示出了航空示例,但是本公开的原理可以应用于其它行业,诸如船舶以及汽车工业。
在本文中呈现的系统和方法可以在生产与保养方法70的任意一个或更多个阶段期间使用。例如,对应于生产过程78的组件或部件可以被类似于飞机72服役时生产的组件或部件的方式制作或制造。同样,例如通过充分加快飞机72的装配或降低飞机72的成本,可以在生产阶段78和80期间一个或更多个设备实施例、方法实施例或其组合。类似地,在飞机72服役时,一个或更多个设备实施例、方法实施例或其组合可以例如但不限于被用于维护与保养86。
为了图示说明和描述的目的,已经介绍了不同的有利实施例的描述,其并不意欲是穷举的或局限于所公开形式的实施例。很多修改和变化对本领域技术人员来说将会是显而易见的。此外,与其它有利实施例相比,不同的有利实施例可以提供不同的优点。所选的实施例或多个实施例被选择和描述,以便更好地解释实施例的原理、实际应用,并使本领域其他技术人员能够理解各种实施例的公开内容,其中适合于特定用途的各种修改是可预期的。
Claims (12)
1.一种支柱(20),其包含:
大致管状的纤维加强的树脂芯(34)
围绕所述芯(34)的外蒙皮(38);以及
围绕所述芯(34)、在所述外蒙皮(38)与所述芯(34)之间的套筒状加强件(36),所述筒状加强件(36)包括相对于所述芯向内的多个波纹脊(46a)以及在所述多个波纹脊(46a)之间的多个区段,所述多个区段的第一曲率匹配所述外蒙皮的第二曲率,其中所述多个波纹脊(46a)具有第三曲率,使得所述多个波纹脊(46a)向下延伸到所述芯的层压的层板(48)内并且抵靠所述芯(34)的所述层压的层板(48)被压紧,并且
其中所述套筒状加强件(36)包括沿缝(44)组装在一起的第一半部和第二半部(36a、36b),所述缝(44)在所述芯(34)的纵向方向上延伸。
2.如权利要求1所述的支柱(20),其中所述套筒状加强件(36)是金属。
3.如权利要求1所述的支柱(20),其中所述缝(44)被布置在围绕所述芯(34)的大体上优化所述管状体(22)的抗弯强度的位置处。
4.如权利要求1所述的支柱(20),其还包含:
包括一对连接销(30)的一对间隔开的端部配合件(24),所述连接销大体上位于第一平面(35)中,并且适合于将所述支柱附接至结构,以及
其中所述缝(44)中的至少一个大体上位于大致垂直于所述第一平面的第二平面(37)中。
5.如权利要求1所述的支柱(20),其中所述套筒状加强件(36)是陶瓷。
6.如权利要求1所述的支柱(20),其中:
所述套筒状加强件(36)是钛,并且具有在其上带有纵向凸起的带状物(47)的内侧表面(45),以及
所述纤维加强的树脂芯(34)是碳纤维加强的塑料。
7.如权利要求1或权利要求5所述的支柱(20),其中所述套筒状加强件(36)包括均具有内侧表面(45)的第一半部和第二半部(36a、36b),所述内侧表面(45)提供有与所述芯(34)接触的脊(46a)。
8.如权利要求7所述的支柱(20),其中:
所述外蒙皮(38)覆盖所述套筒状加强件(36),并且
其中使所述套筒状加强件与所述芯(34)共结合,并且与所述外蒙皮共结合。
9.一种制作支柱(20)的方法,其包含:
制造复合材料层压板芯(34);
制造套筒状加强件(36);
在所述芯上面组装所述加强件;以及
在所述套筒状加强件上面制造外蒙皮(38);
其中所述套筒状加强件(36)围绕所述复合材料层压板芯(34)、在所述外蒙皮(38)与所述复合材料层压板芯(34)之间,所述筒状加强件(36)包括相对于所述复合材料层压板芯向内的多个波纹脊(46a)以及在所述多个波纹脊(46a)之间的多个区段,所述多个区段的第一曲率匹配所述外蒙皮的第二曲率,其中所述多个波纹脊(46a)具有第三曲率,使得所述多个波纹脊(46a)向下延伸到所述复合材料层压板芯的层压的层板(48)内并且抵靠所述复合材料层压板芯(34)的所述层压的层板(48)被压紧,并且
其中在所述芯(34)上面组装所述套筒状加强件(36)包括,制造第一半部(36a)和第二半部(36b),以及将所述半部放在所述芯上面并沿所述芯的纵向方向布置所述半部之间的缝(44)。
10.如权利要求9所述的方法,其还包含:
使所述套筒状加强件(36)与所述芯(34)共结合,并且与所述外蒙皮(38)共结合。
11.如权利要求9或权利要求10所述的方法,其中:
制造所述套筒状加强件(36)包括,在构件的内侧表面(45)上形成波纹(46),
制造所述复合材料层压板芯(34)包括,铺设纤维加强的树脂的层板(48),以及
在所述芯上面组装所述套筒状加强件包括,将所述构件放在所述芯上,其中所述波纹倚着所述芯的铺设的层板。
12.如权利要求11所述的方法,其还包含:
固结并固化所述芯(34),以及
在所述固结期间,利用所述构件上的所述波纹(46)来控制所述层板(48)的起皱。
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