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公开(公告)号：US5547737A
公开(公告)日：1996-08-20
申请号：US303671
申请日：1994-09-09
CPC分类号： B64C1/12 , B29D24/008 , B32B3/20 , B32B5/28 , C04B35/83 , E04C2/3405 , B64C2001/0072 , E04C2002/345 , E04C2002/3477 , Y02T50/433 , Y10T428/24661 , Y10T428/24744
摘要： A method for the manufacture of a light-weight panel, e.g. for aircraft, comprising preparing a panel preform having a pair of surface members or skins (29, 30) separated and supported by an internal core (26-28) in which spaces or interconnected pores provide vents to an edge of the panel, the wall surface members and the core comprising fibrous material, which may be carbon fibre, and using a pyrolysis process such as CVD to form a pyrolyric matrix around the fibres within the fibrous material, there being a flow of gas through the vents during the pyrolysis process.
摘要翻译： 一种用于制造轻质面板的方法，例如， 用于飞行器，包括制备具有一对表面构件或表皮（29,30）的面板预成型件，所述表面构件或表面（29,30）由内部芯（26-28）分隔和支撑，在所述内部芯（26-28）中空间或互连的孔向所述面板的边缘提供通风口， 表面构件和包含纤维材料的芯，其可以是碳纤维，并且使用诸如CVD的热解方法在纤维材料内的纤维周围形成热解基质，在热解过程期间存在通过通气孔的气流。
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公开(公告)号：US5599603A
公开(公告)日：1997-02-04
申请号：US202890
申请日：1994-02-28
CPC分类号： C04B35/83 , B32B1/08 , B32B19/00 , B32B27/02 , B32B5/26 , B32B7/08 , D04H1/4242 , D04H1/46 , D04H1/52 , F16D69/023 , C04B2235/5268 , C04B2235/604 , Y10T428/21 , Y10T428/213 , Y10T428/218 , Y10T428/30 , Y10T442/682
摘要： In a method of making a carbon fibre preform such as for use in the manufacture of a friction disc a compressible body of carbon fibre or carbon fibre precursor material is acted upon by compressing means to compress the body to a required thickness and then operated upon by means such as a barbed needle-punch needle for a stitching thread which penetrates substantially the whole thickness of the body whereby the compressed preform may be removed from action by the compressing means in a free-standing and compressed state. If the method uses carbon fibre precursor material, that is then subjected to carbonization.
摘要翻译： 在制造用于制造摩擦盘的碳纤维预成型件的方法中，碳纤维或碳纤维前体材料的可压缩体通过压缩装置作用，以将本体压缩至所需厚度，然后由 用于缝合线的有刺刺针针的装置，其穿透主体的整个厚度，由此压缩预成型件可以通过压缩装置以独立和压缩的状态从动作中移除。 如果该方法使用碳纤维前体材料，则将其进行碳化。
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公开(公告)号：US4780363A
公开(公告)日：1988-10-25
申请号：US138292
申请日：1987-12-28
IPC分类号： D01F9/14 , D01F11/14 , D04H1/42 , D04H1/4242 , D04H1/645 , D04H3/002 , D04H3/02 , D04H3/04 , D04H3/10 , D04H3/105 , B32B5/12
CPC分类号： D04H3/105 , D01F11/14 , D04H1/4242 , D04H1/4374 , D04H1/645 , D04H3/002 , D04H3/02 , D04H3/04 , D04H3/10 , Y10T428/24058 , Y10T428/30 , Y10T442/643 , Y10T442/667
摘要： A sheet of parallel carbon or carbon-precursor filaments is supported by a carrier sheet of fugitive backing material and needle punched. The fugitive backing material is subsequently destroyed leaving displaced or broken portions of the filaments entangled together to provide a stable sheet for composite manufacture, particularly for reinforcement of a carbon-carbon composite.
摘要翻译： 平行的碳或碳前体细丝由一片短片背衬材料的支撑片支撑并进行针刺。 随后破坏了挥发性背衬材料，将长丝的移动或断裂部分缠结在一起，以提供用于复合制造的稳定片材，特别是用于增强碳 - 碳复合材料。
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公开(公告)号：US5503893A
公开(公告)日：1996-04-02
申请号：US246228
申请日：1994-05-18
IPC分类号： B29B11/16 , B29C70/24 , B29K105/08 , B29K307/04 , B32B5/00 , B32B5/02 , B32B5/06 , B32B5/12 , B32B7/02 , C04B35/52 , C04B35/83 , D01F9/12 , D04H1/4242 , D04H1/498 , D04H1/593 , D04H13/00 , F16D69/02 , B32B31/16 , B32B31/26 , D04H5/02
CPC分类号： D04H1/4242 , B29C70/24 , B32B7/02 , C04B35/83 , D04H1/498 , D04H1/593 , D04H13/00 , F16D69/023 , B29K2307/00 , Y10S376/904 , Y10T428/24099 , Y10T428/24107 , Y10T428/24132 , Y10T428/24942 , Y10T428/30 , Y10T442/662 , Y10T442/687
摘要： Method of fabricating a multi-ply carbon fibre fabric, preform or composite material from a layer of unidirectionally aligned carbon fibres of ultra-high modulus and a layer of low modulus carbon fibre comprising the steps of: arranging in superimposed relationship the layer of unidirectionally aligned carbon fibres of ultra-high modulus and the layer of low modulus carbon fibres so that at least a substantial number of the fibres of low modulus are disposed transversely of the fibres of the ultra-high modulus fibre layer, and connecting the two layers by interlacing fibres of the layer of low modulus fibres with those of the layer of ultra-high modulus fibres by needle-punching using felting needles orientated and configured so that their barbs snag only the low modulus fibres during passage through the layers.
摘要翻译： 从超高模量的单向排列碳纤维层和低模量碳纤维层制造多层碳纤维织物，预成型件或复合材料的方法，包括以下步骤：以叠加关系布置单向对准的层 超高模量的碳纤维和低模量碳纤维层，使得至少相当数量的低模量的纤维横向于超高模量纤维层的纤维设置，并且通过交织连接两层 低模量纤维层的纤维与超高模量纤维层的纤维通过使用定向和构造的毡针进行针刺冲切，使得它们的倒钩在通过层期间仅阻挡低模量纤维。
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公开(公告)号：US5503254A
公开(公告)日：1996-04-02
申请号：US128571
申请日：1993-09-30
CPC分类号： F16D55/40 , F16D55/36 , F16D65/126 , F16D69/023 , F16D2055/0058 , F16D2069/002 , F16D65/127
摘要： An aircraft disc stack (1) comprises a plurality of interleaved stator and rotor discs (3,4) keyed respectively to a torque tube (5) and a wheel hub (not shown). The stack (1) further comprises bi-functional friction/load transmitting discs in the form of end stator discs (10,13). These discs (10,13) are subject to uneven loading because the non-friction surfaces (12,15) are in use compressed on areas less than the load bearing areas of the opposing friction faces (11,14). This can lead to premature disc failure and in the past load spreader plates have been used to distribute loading over these areas to minimize the risk of failure. In this invention portions of the load bearing areas of non-friction surfaces (12,15) are toughened ie: material underlying these surfaces is toughened, to increase their resistance to deformation, fracture and/or wear thereby removing the need for additional load spreader plates which were hitherto required.
摘要翻译： 飞机盘堆叠（1）包括分别键合到扭矩管（5）和轮毂（未示出）的多个交错的定子和转子盘（3,4）。 堆（1）还包括端定子盘（10,13）形式的双功能摩擦/载荷传递盘。 由于非摩擦表面（12,15）在比相对的摩擦面（11,14）的承载区域小的区域上被压缩，所以这些盘（10,13）承受不均匀的载荷。 这可能导致过早的盘故障，并且在过去的负载中，吊具板已经用于在这些区域上分配负载以最小化故障的风险。 在本发明中，非摩擦表面（12,15）的承载区域的部分是增韧的，即：这些表面下面的材料被增韧，以增加它们对变形，断裂和/或磨损的抵抗力，从而消除对额外负载撒布机的需要 迄今为止所需的板材。
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公开(公告)号：US5360500A
公开(公告)日：1994-11-01
申请号：US190615
申请日：1994-02-02
CPC分类号： B64C1/12 , B29D24/008 , B32B3/20 , B32B5/28 , C04B35/83 , E04C2/3405 , B64C2001/0072 , E04C2002/345 , E04C2002/3477 , Y02T50/433 , Y10T428/24661 , Y10T428/24744
摘要： A method for the manufacture of a light-weight panel, e.g. for aircraft, comprising preparing a panel preform having a pair of surface members or skins separated and supported by an internal core in which spaces or interconnected pores provide vents to an edge of the panel, the wall surface members and the core comprising fibrous material, which may be carbon fiber, and using a pyrolysis process such as CVD to form a pyrolytic matrix around the fibers within the fibrous material, there being a flow of gas through the vents during the pyrolysis process.
摘要翻译： 一种用于制造轻质面板的方法，例如， 用于飞机，包括制备具有一对表面构件或表皮的面板预成型件，所述表面构件或表皮由内部芯部分隔并支撑，其中空间或互连的孔向所述面板的边缘提供通风口，所述壁表面构件和所述芯包括纤维材料， 可以是碳纤维，并且使用诸如CVD的热解方法在纤维材料内的纤维周围形成热解基质，在热解过程期间存在通过通气孔的气流。
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