CN1269746A - 具有极向机织基材的近网状针刺碳预制品及其制造方法 - Google Patents
具有极向机织基材的近网状针刺碳预制品及其制造方法 Download PDFInfo
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Abstract
本发明提供近网状碳预制品,它包括许多碳纱线的机织物,所述机织物具有螺旋形状和可调节的纤维定向分布,所述机织物依次铺置,形成近网状预制品,对所述织物的每层都进行针刺,制成层间强度有所增强、纤维定向分布可调节的近网状预制品。本发明也揭示了制造具有极向机织基材的近网状碳预制品的方法。
Description
发明的背景
本发明总的来说涉及碳基材和采用该基材的预制品的制造方法,具体地说,涉及极向机织物针刺基材和采用该基材生产摩擦盘的碳预制品的制造方法。
用于飞机或汽车的制动盘要求耐热—机械性能高的和耐磨的材料。就某些应用而言,由于石棉具有耐热性能,所以可使用石棉。尽管常规的碳制动器产品成本高,而且历史上的应用仅限于航空或赛车,但除了石棉,由于碳具有优良的耐热性能,也可以使用碳。
通常,碳纤维基材或碳的前体可以用来制造常规的碳/碳零件,该零件具有足够高的耐热值,可用于例如飞机制动体系,这些常规的零件需要复杂的耗时工艺来制造碳含量足够高以提供必要的耐高温性能的零件。这些常规的碳/碳零件由于制造工艺复杂,所以成本高。就用于制造常规碳零件的基材而言,有许多不同的类型,包括非连续性碳纤维模塑复合、气流成网碳纤维无纺布基材、机织碳纤维基材、或编织碳纤维基材。
为了由碳纤维基材制造常规的碳零件,使用许多碳纤维前体例如聚丙烯腈(PAN)纤维层。这些基材是片材,必须切成特定形状例如制动盘,由于基材通常是不能回收的,所以会浪费一部分基材。这些基材可以彼此叠压,达到所要求的厚度,叠起来的基材可以由针刺结合起来,或在基材层之间掺杂碳纤维使基材彼此固结起来。该基材固结成预制品。接着,预制品可以分批进行碳化,将预制品置于800-1100℃的烘箱内,使基材的纤维烧焦,提高预制品的碳含量。接着这些预制品可以通过采用化学蒸汽浸渗(CVI)工序,将碳原子沉积在预制品的碳纤维上,使之具有额外的碳原子。在CVI工序中,将预制品置于一个室内,脱除室内空气,将含碳气体例如甲烷引入室内,当经受一定温度时,会释放碳原子并固定/浸渗入预制品。CVI工序可以提高碳的含量和预制品的密度。接着,预制品可以进行热处理使碳原子重新定向为能量更高的有利构型,以改善例如物理性能和机械性能,再用抗氧剂进行处理,以形成成品碳零件。
如上所述,常规的预制品成形工艺和常规的碳零件存在几个问题。分批碳化的工艺慢,而且耗时,需要数小时或数天,这增加了零件的成本。由于进行碳化所必需的炉子不能用于其他用途,所以这些炉子又增加成本。另外,在模子裁切和成形加工期间,自预制品裁掉的任何材料通常都不能重复使用,这是因为没有合适的方法将这些碎屑材料再循环用于预成形制造工序中。因此,由于存在上述问题,常规的预制品制造碳零件成本过高而不能用于大多数商业用途。
编织是另一种常规的试图降低每件预制品产生的废料的方法。管状编织物可以坍缩形成平板类型,平板可螺旋地卷绕以形成废料有所减少的盘状预制品,这是由于盘不是自片材裁切下来。采用此方法时,纤维在预制品内的分布是不均匀的。
另一种常规的碳纤维基材是使用合适粘合剂浸渍,浸渍过的基材可以在热和压力下压成近网状的预制品。接着,通过粘合剂凝缩成碳,将预制品分批碳化,使粘合剂烧焦形成碳。粘合剂可以是由马来酸酐催化的液态糠醇聚合物。该基材需要分批碳化的工艺步骤,将粘合剂烧焦。另一种用碳纤维制备碳零件的基材,是将氧化的聚丙烯腈(PAN)纤维经碳化,形成可以实施化学蒸汽浸渗(CVI)工艺的碳预制品。该基材也需要碳化步骤。
这些用来制造碳零件的常规材料,需要分批碳化的步骤,该步骤慢,增加了最终零件的成本,而且需要昂贵的碳化炉。没有任何一种常规材料可以在整个预制品上提供可控制的、均匀的、一致的纤维取向分布。常规预制品也浪费基材,增加预制品成本。由于存在这些缺陷,所以常规预制品制成的是成本太高而不能用于大多数商业用途的碳零件,而且不能提供足够均匀的纤维分布。
因此,目前需要有一种对由极向机织基材制成的预制品、采用可避免已知基材、工艺和碳预制品的这些和其他问题的基材制造碳预制品的方法,这正是本发明的目的。
发明的概述
本发明提供由极向机织基材制造的预制品,该基材可制备具有几方面优点的近网状碳预制品。将预制品修整成盘形状有关的基材用量,可以通过制成不需修整的近网状极向机织基材而下降。另外,用碳纤维形成预制品,减免了耗时和昂贵的碳化步骤。极向机织基材具有一定的纤维取向度和定位,当与合适的针刺工艺参数结合,就可制成在整个预制品内纤维均匀分布的预制品,这可以用于摩擦盘例如飞机制动器。
本发明还提供具有一对可机织在一起的垂直定向碳纱线的极向机织基材。许多碳纤维可以与纱线缠绕,这样就可以制得带有缠绕的碳纤维的织物。此织物可以是极向机织物,使得织物可以具有螺旋形状,而且可以通过铺置螺旋状的极向机织物层制成近网状盘预制品。根据所要求的预制品的性能,可以使用不同的机织图案。另外,不同梯度的纱线可织进织物中,在整个预制品体积内纤维可均匀分布,形成均相预制品。极向机织物可以绕成可针刺以增强预制品结合力、复合物的层间强度和预制品密度的盘状预制品。可以调节针刺参数以改变预制品乃至复合物的性能。
因此,根据本发明,提供包含带有许多碳纱线的机织物的近网状碳预制品,该机织物呈螺旋形状,并具有可调节的纤维取向分布,该机织物依序盘绕铺置成近网状预制品,对该织物的每层都进行针刺,以制成纤维取向分布可调节的近网状预制品。也揭示了制造带有极向机织基材的近网状碳预制品的方法。
附图的简要说明
图1根据本发明采用极向机织基材制造近网状碳零件的方法的流程说明图;
图2根据本发明制造极向机织基材的工艺图;
图3A基本的机织图案的说明图;
图3B和3C从织物反面所看到的斜纹机织图案的说明图;
图3D和3E从织物反面所看到的缎纹机织图案的说明图;
图4带有末端具有细微梯度结构的经纱,并可以根据本发明用来制造极向机织预制品的极向机织基材的说明图;
图5带有梯度结构的纬纱,并可以根据本发明用来制造极向机织预制品的极向机织基材的说明图;
图6根据本发明固结极向机织物基材以形成预制品的方法的说明图;
图7按本发明固结的预制品的剖面图。
优选实施方式的详细说明
本发明尤其适用于用极向机织基材生产用于制造摩擦盘的碳预制品。本文将描述本发明。然而,通过本发明将会认识到本发明的基材、预制品和方法还具有更大的实用性。
图1是根据本发明采用极向机织碳纤维基材制造碳预制品的方法20的流程图。首先,可以在步骤22中确定要制造的具体预制品的各种设计标准,并可以选择各工艺步骤合适的标准和参数,以满足设计标准的要求。例如,如下所述对极向机织预制品的性能进行改进,制成性能略微不同的预制品,可以改进针刺参数,或改进所选择的用以制成极向机织物的纱线。接着,在步骤24中,可以如下所述参照图2-6,制造极向机织基材。
极向机织基材可以由碳纤维形成,这样实际预制品可不需要碳化,因为碳纤维已经预先碳化过。极向机织基材可以包含许多碳纤维、碳纤维前体,例如PAN纤维、陶瓷纤维或碳化度不同的碳纤维。按本发明,可以采用几种不同类型的含有碳纤维的碳纱线制造极向机织预制品。第一种碳纱线含有彼此基本平行的略微加拈的连续碳纤维长丝。另一种碳纱线含有许多非连续纤维。非连续纤维可以通过将连续纤维长丝拉断成碳的碎片,并使碳的碎片由短效材料固定在一起而形成,但它们受热后会从预制品上脱落。短效材料可以是聚乙烯醇(PVA)、聚丙烯或聚酯。接着,这些碳纱线可以如下所述通过机织成极向机织物,再用来制成极向机织近网状预制品。短效材料可以在CVI致密化步骤期间除去。
一旦制成近网状极向机织基材,在步骤26中,极向机织基材可以呈螺旋状铺置以形成所要求厚度的近网状盘,接着,极向机织物层可以通过如下所述的针刺工艺以几种不同方式压实,参照图7和8。针刺工艺可以使一些纤维自一个特定层贯穿至另一层重新定向,使得一些层内和层间的纤维沿Z平面方向重新定向,并与一些来自另一层的纤维相互混合。这种基材叠层纤维间的混合增强了复合物的层间强度。接着,压实的预制品可以在步骤28中致密化,以制成致密零件,其中碳原子可以填充预制品碳纤维之间的自由体积,使零件密度增加。通常,使用化学蒸汽浸渗(CVI)工艺加入碳原子,其中预制品置于已加热的室内,排出室内空气,含有碳的气体例如甲烷充入室内,目的是使甲烷中的碳可以沉积和浸渍在预制品上。致密化预制品也可以在步骤29中进行加工。最后,在步骤30中,可以将抗氧剂层加到致密化零件暴露出的表面上。抗氧剂层是为了防止碳零件的表面氧化。下面将说明制造本发明的用于近网状碳预制品的极向机织物基材的方法。
图2是按本发明制造极向机织基材的工艺图。如上所述,两套叫作经纱和纬纱的垂直定向的碳纱线经上述常规机织机40和常规机织工艺、机织而结合起来。根据本发明,带有连续和非连续纤维的两种碳纱线都可以用来制造极向机织物。一对锥形辊42、44可以是机织机的卷绕装置。由于每个辊子的头部46和底部48之间的卷绕速度不同,辊子可以使织物具有弧度。每个辊子的头部和底部之间的速度差会使形成的织物50具有扁平螺旋形状。所形成的织物的内径52和外径54由辊子42、44的几何尺寸和辊子内织物的位置决定。螺旋状织物的内径可以由辊子的头部形成,而外径可以由辊子的底部形成。织物的经纱可以沿螺旋的长度定向,而纬纱或填充纱可以定向在与螺旋轴垂直的平面内。由此,经纱是周边定向,而纬纱是径向定向,这使得经纱和纬纱在它们交叉点处是垂直的。碳纤维就是这样分布于整个织物内。
为了织造极向机织物,要单个控制每根末端纱的长度和张力,目的是使纱不反卷,而且可以达到所要求的螺旋织物内径和外径。除了使用碳纱线,其他的机织工序都是常规性的。对于该极向机织物,常规机织机是合适的。
可制成一定尺寸、性能和几何尺寸的织物,以满足所要求的复合物性能。通过使用如下所述的各种机织图案或如下所述的不同梯度的极向机织物(参照图4-5),可以调节尺寸大小、性能和参数。制成的盘的宽度可以通过在织机上调节织物宽度来进行调节,该宽度与致密化之前的预制盘尺寸一致,并可根据盘尺寸容易地进行调节。可能影响所形成的预制品和碳预制品性能的各种机织图案,将在下面说明。
图3A-3E说明了各种可用来改变极向机织物和所形成的预制品和零件的性能的机织图案。机织图案也可以根据针刺参数进行选择,例如针的定向和针剌密度。这些参数与织物图案的组合可以形成具有不同性能的预制品和碳零件。图3A说明了易于制造、简单、平面的基本机织图案,图3B和3C说明了织物各边的斜纹机织图案。该机织图案可制成比简单机织图案更光滑的可提高预制品强度的织物,但可能比较难于制造,并会增加预制品的总成本。图3D和3E说明了织物各边的五综缎机织图案。缎机织图案制成最光滑、最平坦的织物,以制成更强固的预制品,但可能更难于制造,而且会进一步增加预制品的成本。对这些机织图案的选择,依赖于所要求的预制品的特定性能。下面参照图4和5,说明制造结构均匀的极向机织物基材的方法。
极向机织物和所形成的预制品和零件的一个重要性能是在整个预制品中形成均匀的结构。均匀的结构可以由极向机织物和极向机织基材由于针刺而产生的固结而得到。极向机织可在织物整个宽度上(即,自内径至外径)形成均一的纤维体积分数,这可以产生如下所述的均匀的结构,参照图4-5。因为盘式预制品自内到外边缘碳纱线的密度在降低,所以常规的极向机织物成形方法在织物的宽度上形成不一致的面密度,下面将说明结构均匀的极向机织物的形成。它可以有几种不同的技术,下面将说明两种。
在图4所示的一个实施方式中,调节极向机织物74中经纱70的纱线线密度(也称为特克斯),以保持均一的纤维体积分数。这称为带有末端具有细微梯度结构的经纱的极向机织物。如图所示,经纱的尺寸可以自织物的内径至织物的外径逐渐增加,以保持均一的纤维体积分数。该实施方式要求严格地控制纱线厚度。下面将说明制造结构均匀的极向机织物的第二个实施方式。
图5说明了具有纬纱梯度结构的极向机织物76,其中自内径至外径的每平方英寸上的纬纱数是增加的,以保持恒定的织物面密度。如图所示,朝向螺旋织物的外径,可以在织物中加入另外的纬纱78,这使得即使在织物的外径处,每平方英寸上的纬纱数也保持恒定。尽管在纬纱72之间只显示出一根额外的纬纱,本发明并不限制额外纬纱的具体数目。例如,经纱70对纬纱72的分布比率在整个螺旋状织物内可以保持在1∶1。所要求的纬纱的加入可以通过将合适的纬纱织入织物的合适部位来实现。另外,不同长度的纬纱也可以插入织物内。如果需要,也可以将该纬纱梯度结构与上述方法结合起来。下面说明将本发明的极向机织物压实形成碳预制品的方法。
图6按本发明将极向机织螺旋织物压实形成碳预制品的方法的说明图,图7是压实的预制品的说明图。如图所示,盘式预制品可以通过叠压许多层的极向机织螺旋织物100、直至达到所要求的厚度而制成。这些织物层可以由带有许多剌针106的针刺机102进行针刺。压实预制品的工序(即针刺)可以以几种方式实现。具体地,极向机织物可以非连续地提供给针刺机,使织物的每一层是分离的,或极向机织物可以连续地供应给针刺机,这样可提高针刺的速度。另外,可以对每一层织物进行一次针刺,也可以对几层织物进行一次针刺,或对所有层同时进行针刺。
在一个实施方式中,极向机织物的非连续层可以供给针刺机,目的是对织物的第一层和第二层进行针刺,接着另外的每一圈/层也可以进行针刺。此外,当没有另外的层加到预制品上之后,整个预制品也可以进行针刺或多次针刺。针刺可以将极向机织螺旋织物的层结合起来,因为在针刺期间、正如本行业所已知的那样,每层内一些纤维可以自基材的特定层贯穿至另一基材层进行重新定向,使得一些基材内和基材间的纤维沿Z方向定向,并与来自其他层的纤维进行混合,这会增强所形成的预制品的层间强度。
图7是根据本发明制成的盘式预制品108的剖面图,由于上述的梯度结构和针刺,它可以具有三维的纤维定向分布。盘式预制品内的许多纤维110大多在垂直于盘轴的平面内定向,沿轴的周边和径向铺展。由于针剌,相当量的纤维112沿轴定向。盘式预制品内的纤维定向可以根据所要求的碳零件成品的性能而进行调节,例如,沿径向和周边方向定向的碳纤维可以采用上述技术进行调节,参照图4-5。多层极向机织物也可以进行预针刺,彼此在顶部叠压,并再次针刺以进一步压实预制品。对于薄型单层极向机织物,可在几层顶部彼此叠压并针刺。
在第二实施方式中,为了提高近网状预制品针剌机的生产率,可以以连续工艺的方式制造盘式预制品,其中极向机织物可以依次一层层地连续喂入针刺机内。首先,对应于极向机织物一层的单层放置在针刺机内的接收碗内,将第二层叠压在第一层的顶部,并针刺到第一层。然后,将第三层叠压至前两层顶部,而且第三层可以针刺入前两层内,如此下去,直至获得所要求的预制品厚度。针刺期间针的刺入深度可以基本保持在第三层之后的每个增加层内,这使得预制品整个厚度上的碳纤维的均匀分布有所提高。一旦没有另外的层加到预制品上,也可以实施一次或多次最终针刺操作,目的是保持预制品内一致的纤维分布。
为了制造具有所要求性能的近网状预制品,可以选择合适的针刺参数。可以调节的针刺参数可包括,例如针的具体类型、每层针剌密度(为针刺机每分钟针剌数的函数)、织物进入和离开针刺机的速率、针刺机内针的数目、针板的针密度梯度。另一个可调节的参数是针的刺入深度。针剌密度可以在约5-500个针刺/厘米2的范围内变化。过多的针剌会损害碳纤维,而过少的针剌不足以强固预制品。针的刺入深度由自预制品的顶部至针尖进行测量,它可以根据预制品的厚度和所要求的针刺密度在0-20毫米范围内变化。这些不同的针刺特性会影响预制品的完整性,因为较多的针刺会增加沿Z方向重新定向的碳纤维的数量,这会增强预制品的结合力。近网状碳预制品可以具有约占预制品23-33%的纤维体积分数。然而,较低和较高的数值也是可以达到的。还应当注意的是:自内径至外径的Z纤维的数量可以通过对剌针类型、针剌密度和刺入深度的选择而确定。
下面将说明根据本发明制成的极向机织物和预制品的示例。示出的预制品约为3/4英寸(0.75”)厚,可用于要求耐高温性能的飞机制动器。可使用12000长丝的碳纱线,这些纱线可以用来制造极向机织物。极向机织物可以具有平面机织图案,以提供结构的平衡,并便于针刺。织物也可以具有纬纱梯度,使纤维在织物内均匀分布。织物的面密度约为600克/米2。为了制成所要求的0.75英寸厚的预制品,要使用几十层的织物。预制品可以通过将织物的前两层针刺起来、接着将叠加的每层都针刺到基材上而形成。为了此特定的预制品,每层针刺15针/厘米2的针刺密度和17毫米的刺入深度。选择这些参数是为了提供均匀的预制品的整体性以及层间充分的粘合。所形成的预制品是近似网状,并沿其整个宽度和厚度具有均匀的纤维体积分数。在此实施例中,纤维体积约占整个预制品体积的27%。
虽然上述说明是参照本发明的具体实施方式进行的,本行业的普通技术人员将会认识到:在不脱离本发明原理、精神基础上,这些实施例是可以变化的,而这些都由所附属的权利要求所限制。
Claims (23)
1.针刺近网状碳预制品,它包含含有许多碳纱线的机织物,所述机织物具有螺旋形状和可调节的纤维定向分布,所述机织物依次铺置,形成近网状预制品,对所述织物的每层都进行针刺以制成层间强度有所增强、纤维定向分布可调节的近网状预制品。
2.如权利要求1所述的预制品,其中所述的螺旋状织物由一对织物经过的辊子所制成,所述的一对辊子是锥形辊子,这样可使织物的内径与外径不同。
3.如权利要求1所述的预制品,其中所述的织物包含平面机织图案。
4.如权利要求1所述的预制品,其中所述的织物包含斜纹机织图案。
5.如权利要求1所述的预制品,其中所述的织物包含缎机织图案。
6.如权利要求1所述的预制品,其中所述的每根碳纱线都含有连续的碳纤维长丝。
7.如权利要求1所述的预制品,其中所述的每根碳纱线都含有许多非连续的碳纤维长丝和包复在所述非连续碳纤维长丝上的短效材料。
8.如权利要求1所述的预制品,其中所述的织物在织物宽度上具有梯度,所述梯度包括自预制品的内径至外径纱线的尺寸有所增加。
9.如权利要求1所述的预制品,其中所述的织物包含与许多纬纱垂直定向的许多经纱,其中所述的织物还在织物宽度上具有梯度,梯度包括自预制品的内径至外径纬纱数目有所增加。
10.如权利要求1所述的预制品,其中所述的针刺包括使预制品每层的刺入深度基本恒定的步骤。
11.制造近网状碳预制品的方法,它包括:
提供带有许多碳纱线的机织物,该机织物具有螺旋形状;
将螺旋状织物的一层放置于前一螺旋层的顶部;以及
将所述层针刺到所述前层上,以将所述层内的碳纤维与所述前层内的碳纤维混合,加强复合物的层间强度和预制品的整体性。
12.如权利要求11所述的方法,它还包括连续供给所述织物层,制成许多预制品。
13.如权利要求11所述的方法,它还包括采用一对织物经过的辊子制成所述螺旋状织物,所述的一对辊子是锥形辊子,这样可使织物的内径与外径不同。
14.如权利要求11所述的方法,其中所述的织物用平面机织制成。
15.如权利要求11所述的方法,其中所述的织物用斜纹机织图案制成。
16.如权利要求11所述的方法,其中所述的织物用缎机织图案制成。
17.如权利要求11所述的方法,其中所述机织物包括在织物宽度上具有梯度,所述梯度包括织物内纬纱数目增加。
18.如权利要求11所述的方法,其中所述机织物在织物宽度上具有梯度,所述梯度包括自预制品的内径至外径纱线的尺寸增加。
19.如权利要求11所述的方法,其中所述的织物包含在经、纬纱交叉点处与许多纬纱垂直定向的许多经纱,其中所述织物具有梯度,纬纱数目自预制品的内径至外径增加。
20.如权利要求11所述的方法,其中所述的针刺包括使预制品每层的刺入深度基本恒定。
21.如权利要求11所述的方法,其中所述的针刺还包括使所述预制品具有预定的针刺密度。
22.如权利要求21所述的方法,其中所述的预定针刺密度约为5-500针/厘米2。
23.如权利要求11所述的方法,它还包括一次性将许多层织物针刺起来。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US08/924,907 | 1997-09-08 | ||
US08/924,907 US5952075A (en) | 1997-09-08 | 1997-09-08 | Needled near netshape carbon preforms having polar woven substrates and methods of producing same |
Publications (1)
Publication Number | Publication Date |
---|---|
CN1269746A true CN1269746A (zh) | 2000-10-11 |
Family
ID=25450899
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CN98808886A Pending CN1269746A (zh) | 1997-09-08 | 1998-09-02 | 具有极向机织基材的近网状针刺碳预制品及其制造方法 |
Country Status (7)
Country | Link |
---|---|
US (1) | US5952075A (zh) |
EP (1) | EP1023162A4 (zh) |
JP (1) | JP2003526588A (zh) |
KR (1) | KR20010023558A (zh) |
CN (1) | CN1269746A (zh) |
AU (1) | AU9219898A (zh) |
WO (1) | WO1999012733A1 (zh) |
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CN101208191B (zh) * | 2005-06-24 | 2012-10-31 | 斯奈克玛 | 一种复合材料部件用的增强纤维结构和使用这种结构的部件 |
CN106427101A (zh) * | 2016-08-22 | 2017-02-22 | 苏州勤耘纤维集合体科技有限公司 | 一种新型超高密度纤维针刺毡的制备方法 |
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FR2761379B1 (fr) * | 1997-03-28 | 1999-07-09 | Europ Propulsion | Procede de realisation de structures fibreuses annulaires, notamment pour la fabrication de pieces en materiau composite |
US6248417B1 (en) * | 1997-09-08 | 2001-06-19 | Cytec Technology Corp. | Needled near netshape carbon preforms having polar woven substrates and methods of producing same |
US7563504B2 (en) * | 1998-03-27 | 2009-07-21 | Siemens Energy, Inc. | Utilization of discontinuous fibers for improving properties of high temperature insulation of ceramic matrix composites |
EP1379716B1 (en) | 2001-09-12 | 2007-07-18 | Lockheed Martin Corporation | Woven preform for structural joints |
US20040074075A1 (en) * | 2001-11-08 | 2004-04-22 | James Mark C. | Wear resistance in carbon fiber friction materials |
US8486517B2 (en) * | 2008-03-18 | 2013-07-16 | Crawford Textile Fabrications, Llc | Helical textile with uniform thickness |
US8114506B2 (en) * | 2008-03-18 | 2012-02-14 | Crawford Textile Consulting, Llc | Helical textile with uniform thickness |
US8074330B2 (en) * | 2008-08-13 | 2011-12-13 | Goodrich Corporation | Method and system for enabling z fiber transfer in needled preform |
US9017761B2 (en) * | 2009-05-20 | 2015-04-28 | Honeywell International Inc. | Low cost, high density C-C composites densified by CVD/CVI for aircraft friction materials |
US20110033622A1 (en) * | 2009-08-06 | 2011-02-10 | Honeywell International Inc. | Nonwoven preforms made with increased areal weight fabric segments for aircraft friction materials |
US9353816B2 (en) * | 2009-10-09 | 2016-05-31 | Honeywell International Inc. | Low cost, high density aircraft friction materials utilizing low fiber volume nonwoven preforms with pitch densification |
US20110111123A1 (en) * | 2009-11-12 | 2011-05-12 | Honeywell International Inc. | Increased area weight segments with pitch densification to produce lower cost and higher density aircraft friction materials |
FR2953826B1 (fr) * | 2009-12-16 | 2019-10-11 | Safran Landing Systems | Procede de fabrication d'une piece de friction a base de materiau composite c/c |
US20110275266A1 (en) | 2010-05-05 | 2011-11-10 | Goodrich Corporation | System and method for textile positioning |
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JP5598528B2 (ja) * | 2012-11-29 | 2014-10-01 | 株式会社豊田自動織機 | 筒状繊維構造体 |
US9045846B2 (en) | 2012-12-05 | 2015-06-02 | Goodrich Corporation | Spiral textile and system for weaving the same |
DE102013107991A1 (de) | 2013-07-26 | 2015-02-19 | Kraussmaffei Technologies Gmbh | Verfahren zur endkonturgetreuen Herstellung mechanisch hoch belastbarer Kunststoff-Bauteile |
CN104355299B (zh) * | 2014-10-21 | 2016-07-06 | 中南大学 | 一种掺杂碳纤维网及其制备方法 |
US10401028B2 (en) * | 2015-06-05 | 2019-09-03 | Rolls-Royce American Technologies, Inc. | Machinable CMC insert |
FR3042511B1 (fr) * | 2015-10-16 | 2018-04-20 | Hexcel Reinforcements | Tissu aiguillete de faible grammage, son procede de fabrication et son utilisation dans une couche de diffusion pour une pile a combustible |
US10471947B1 (en) | 2018-04-27 | 2019-11-12 | Honeywell International Inc. | Determining estimated remaining use of brake assembly by transceiver |
US10941826B2 (en) | 2018-09-12 | 2021-03-09 | Honeywell International Inc. | Determining estimated remaining use of brake assembly |
CN111909520A (zh) * | 2020-08-14 | 2020-11-10 | 碳元科技股份有限公司 | 低密度定向高导热垫片及其制备方法 |
US20220082144A1 (en) * | 2020-09-14 | 2022-03-17 | Goodrich Corporation | Carbon/carbon composites and methods of making carbon/carbon composites having increased fiber volume |
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FR2643656B1 (fr) * | 1989-02-27 | 1992-02-14 | Brochier Sa | Structure textile en forme de spirale, procede d'obtention et machine a tisser correspondante |
FR2669940B1 (fr) * | 1990-12-03 | 1994-10-21 | Europ Propulsion | Fil forme a partir de fibres refractaires ou de leurs precurseurs et son application a la fabrication de pieces en materiau composite. |
US5392500A (en) * | 1991-12-02 | 1995-02-28 | Societe Europeenne De Propulsion | Process for the manufacture of a fibrous preform formed of refractory fibers for producing a composite material article |
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AU5386496A (en) * | 1995-04-04 | 1996-10-23 | United States of America, as represented by the Secretary, U.S. Department of Commerce, The | Carbon-carbon cylinder block |
FR2741634B1 (fr) * | 1995-11-27 | 1998-04-17 | Europ Propulsion | Procede pour la realisation de preformes fibreuses destinees a la fabrication de pieces annulaires en materiau composite |
-
1997
- 1997-09-08 US US08/924,907 patent/US5952075A/en not_active Expired - Fee Related
-
1998
- 1998-09-02 AU AU92198/98A patent/AU9219898A/en not_active Abandoned
- 1998-09-02 EP EP98944728A patent/EP1023162A4/en not_active Withdrawn
- 1998-09-02 KR KR1020007002206A patent/KR20010023558A/ko not_active Application Discontinuation
- 1998-09-02 WO PCT/US1998/018351 patent/WO1999012733A1/en not_active Application Discontinuation
- 1998-09-02 JP JP2000510594A patent/JP2003526588A/ja active Pending
- 1998-09-02 CN CN98808886A patent/CN1269746A/zh active Pending
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
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CN101208191B (zh) * | 2005-06-24 | 2012-10-31 | 斯奈克玛 | 一种复合材料部件用的增强纤维结构和使用这种结构的部件 |
CN106427101A (zh) * | 2016-08-22 | 2017-02-22 | 苏州勤耘纤维集合体科技有限公司 | 一种新型超高密度纤维针刺毡的制备方法 |
CN106427101B (zh) * | 2016-08-22 | 2018-08-10 | 苏州勤耘纤维集合体科技有限公司 | 一种新型超高密度纤维针刺毡的制备方法 |
Also Published As
Publication number | Publication date |
---|---|
AU9219898A (en) | 1999-03-29 |
US5952075A (en) | 1999-09-14 |
KR20010023558A (ko) | 2001-03-26 |
EP1023162A4 (en) | 2004-05-06 |
JP2003526588A (ja) | 2003-09-09 |
EP1023162A1 (en) | 2000-08-02 |
WO1999012733A1 (en) | 1999-03-18 |
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