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公开(公告)号：US20120312924A1
公开(公告)日：2012-12-13
申请号：US13590970
申请日：2012-08-21
申请人： Edward Atwood Rainous , Barry Lynn Allmon , Jeffre Gerry Loewe , William Clarke Brooks , Lee Alan Blanton , Courtney James Tudor , Vicky Showalter Budinger
发明人： Edward Atwood Rainous , Barry Lynn Allmon , Jeffre Gerry Loewe , William Clarke Brooks , Lee Alan Blanton , Courtney James Tudor , Vicky Showalter Budinger
IPC分类号： B64D15/00
CPC分类号： B64D15/00 , B64D33/02 , B64D2033/0233 , B64D2033/0286 , F01D9/04 , F01D25/02 , F01D25/162 , F02C7/047 , F05D2300/50212
摘要： A leading edge structure for use in an aerospace vehicle includes a body having a flowpath surface which defines a leading edge adapted to face an air flow during operation, and an opposed inner surface. The body is segmented into a plurality of portions having varying thermal properties and/or mechanical discontinuities, so as to promote stress concentrations in ice attached to the flowpath surface.
摘要翻译： 用于航空航天车辆的前缘结构包括具有流动路径表面的主体，其限定了在操作期间适于面对空气流的前缘以及相对的内表面。 主体被分割成具有变化的热性能和/或机械不连续性的多个部分，以促进附着在流路表面上的冰中的应力集中。
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公开(公告)号：US20090272095A1
公开(公告)日：2009-11-05
申请号：US12112660
申请日：2008-04-30
申请人： Edward Atwood Rainous , Barry Lynn Allmon , Jeffre Gerry Loewe , William Clarke Brooks , Lee Alan Blanton , Courtney James Tudor , Vicky Showalter Budinger
发明人： Edward Atwood Rainous , Barry Lynn Allmon , Jeffre Gerry Loewe , William Clarke Brooks , Lee Alan Blanton , Courtney James Tudor , Vicky Showalter Budinger
IPC分类号： F02C7/04
CPC分类号： B64D15/00
摘要： A leading edge structure for use in an aerospace vehicle includes a body having a flowpath surface which defines a leading edge adapted to face an air flow during operation; and a metallic icephobic plating comprising nickel applied to at least a portion of the flowpath surface.
摘要翻译： 用于航空航天车辆的前缘结构包括具有流动路径表面的主体，其限定在操作期间适于面对空气流的前缘; 以及包含施加到所述流路表面的至少一部分的镍的金属冰敷电镀。
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公开(公告)号：US08245981B2
公开(公告)日：2012-08-21
申请号：US12112733
申请日：2008-04-30
申请人： Edward Atwood Rainous , Barry Lynn Allmon , Jeffre Gerry Loewe , William Clarke Brooks , Lee Alan Blanton , Courtney James Tudor , Vicky Showalter Budinger
发明人： Edward Atwood Rainous , Barry Lynn Allmon , Jeffre Gerry Loewe , William Clarke Brooks , Lee Alan Blanton , Courtney James Tudor , Vicky Showalter Budinger
CPC分类号： B64D15/00 , B64D33/02 , B64D2033/0233 , B64D2033/0286 , F01D9/04 , F01D25/02 , F01D25/162 , F02C7/047 , F05D2300/50212
摘要： A leading edge structure for use in an aerospace vehicle includes a body having a flowpath surface which defines a leading edge adapted to face an air flow during operation, and an opposed inner surface. The body is segmented into a plurality of portions having varying thermal properties and/or mechanical discontinuities, so as to promote stress concentrations in ice attached to the flowpath surface.
摘要翻译： 用于航空航天车辆的前缘结构包括具有流动路径表面的主体，其限定了在操作期间适于面对空气流的前缘以及相对的内表面。 主体被分割成具有变化的热性能和/或机械不连续性的多个部分，以促进附着在流路表面上的冰中的应力集中。
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公开(公告)号：US07992823B2
公开(公告)日：2011-08-09
申请号：US12112660
申请日：2008-04-30
申请人： Edward Atwood Rainous , Barry Lynn Allmon , Jeffre Gerry Loewe , William Clarke Brooks , Lee Alan Blanton , Courtney James Tudor , Vicky Showalter Budinger
发明人： Edward Atwood Rainous , Barry Lynn Allmon , Jeffre Gerry Loewe , William Clarke Brooks , Lee Alan Blanton , Courtney James Tudor , Vicky Showalter Budinger
IPC分类号： B64D15/00
CPC分类号： B64D15/00
摘要： A leading edge structure for use in an aerospace vehicle includes a body having a flowpath surface which defines a leading edge adapted to face an air flow during operation; and a metallic icephobic plating comprising nickel applied to at least a portion of the flowpath surface.
摘要翻译： 用于航空航天车辆的前缘结构包括具有流动路径表面的主体，其限定在操作期间适于面对空气流的前缘; 以及包含施加到所述流路表面的至少一部分的镍的金属冰敷电镀。
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公开(公告)号：US20090272850A1
公开(公告)日：2009-11-05
申请号：US12112733
申请日：2008-04-30
申请人： Edward Atwood Rainous , Barry Lynn Allmon , Jeffre Gerry Loewe , William Clarke Brooks , Lee Alan Blanton , Courtney James Tudor , Vicky Showalter Budinger
发明人： Edward Atwood Rainous , Barry Lynn Allmon , Jeffre Gerry Loewe , William Clarke Brooks , Lee Alan Blanton , Courtney James Tudor , Vicky Showalter Budinger
CPC分类号： B64D15/00 , B64D33/02 , B64D2033/0233 , B64D2033/0286 , F01D9/04 , F01D25/02 , F01D25/162 , F02C7/047 , F05D2300/50212
摘要： A leading edge structure for use in an aerospace vehicle includes a body having a flowpath surface which defines a leading edge adapted to face an air flow during operation, and an opposed inner surface. The body is segmented into a plurality of portions having varying thermal properties and/or mechanical discontinuities, so as to promote stress concentrations in ice attached to the flowpath surface.
摘要翻译： 用于航空航天车辆的前缘结构包括具有流动路径表面的主体，其限定了在操作期间适于面对空气流的前缘以及相对的内表面。 主体被分割成具有变化的热性能和/或机械不连续性的多个部分，以促进附着在流路表面上的冰中的应力集中。
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公开(公告)号：US08333558B2
公开(公告)日：2012-12-18
申请号：US12042692
申请日：2008-03-05
申请人： Scott Roger Finn , Deepali Bhate , Curt Brian Curtis , Stephen Mark Whiteker , Qi Zhu , Lee Alan Blanton , Edward Atwood Rainous
发明人： Scott Roger Finn , Deepali Bhate , Curt Brian Curtis , Stephen Mark Whiteker , Qi Zhu , Lee Alan Blanton , Edward Atwood Rainous
IPC分类号： F01D21/00
CPC分类号： F01D21/045 , F05D2230/90 , F05D2300/21 , F05D2300/601 , F05D2300/603 , Y02T50/67 , Y02T50/672 , Y10T29/49323
摘要： A containment case comprises a composite core, with an inner surface, and at least one ceramic layer integrated with the composite core. The at least one ceramic layer is bonded to the inner surface of the composite core with a resin. In another embodiment, a containment case comprises a composite core, with an inner surface, and a hybrid material comprising at least one ceramic material and at least one non-ceramic material. The hybrid material is disposed on the inner surface of the composite core. The hybrid material is bonded to the inner surface of the composite core with a resin. A method of fabricating a containment case includes the steps of disposing one or more layers of ceramic fabric on an inner surface of a composite core, infusing the composite core and the one or more layers of ceramic fabric with resin, and curing the resin.
摘要翻译： 容纳壳体包括具有内表面的复合芯和与复合芯一体化的至少一个陶瓷层。 至少一个陶瓷层用树脂粘合到复合芯的内表面上。 在另一个实施例中，容纳壳包括具有内表面的复合芯和包含至少一种陶瓷材料和至少一种非陶瓷材料的混合材料。 混合材料设置在复合芯的内表面上。 混合材料用树脂粘合到复合芯的内表面上。 一种制造容纳壳体的方法包括以下步骤：在复合芯的内表面上设置一层或多层陶瓷织物，将树脂复合芯和一层或多层陶瓷织物浸渍，并固化树脂。
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公开(公告)号：US20090226310A1
公开(公告)日：2009-09-10
申请号：US12042692
申请日：2008-03-05
申请人： Scott Roger Finn , Deepali Bhate , Curt Brian Curtis , Stephen Mark Whiteker , Qi Zhu , Lee Alan Blanton , Edward Atwood Rainous
发明人： Scott Roger Finn , Deepali Bhate , Curt Brian Curtis , Stephen Mark Whiteker , Qi Zhu , Lee Alan Blanton , Edward Atwood Rainous
CPC分类号： F01D21/045 , F05D2230/90 , F05D2300/21 , F05D2300/601 , F05D2300/603 , Y02T50/67 , Y02T50/672 , Y10T29/49323
摘要： A containment case comprises a composite core, with an inner surface, and at least one ceramic layer integrated with the composite core. The at least one ceramic layer is bonded to the inner surface of the composite core with a resin. In another embodiment, a containment case comprises a composite core, with an inner surface, and a hybrid material comprising at least one ceramic material and at least one non-ceramic material. The hybrid material is disposed on the inner surface of the composite core. The hybrid material is bonded to the inner surface of the composite core with a resin. A method of fabricating a containment case includes the steps of disposing one or more layers of ceramic fabric on an inner surface of a composite core, infusing the composite core and the one or more layers of ceramic fabric with resin, and curing the resin.
摘要翻译： 容纳壳体包括具有内表面的复合芯和与复合芯一体化的至少一个陶瓷层。 至少一个陶瓷层用树脂粘合到复合芯的内表面上。 在另一个实施例中，容纳壳包括具有内表面的复合芯和包含至少一种陶瓷材料和至少一种非陶瓷材料的混合材料。 混合材料设置在复合芯的内表面上。 混合材料用树脂粘合到复合芯的内表面上。 一种制造容纳壳体的方法包括以下步骤：在复合芯的内表面上设置一层或多层陶瓷织物，将复合芯和一层或多层陶瓷织物注入树脂，并固化树脂。
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公开(公告)号：US07867566B2
公开(公告)日：2011-01-11
申请号：US11925331
申请日：2007-10-26
申请人： Lee Alan Blanton , Gregory Joseph Meibers , Robert Paul Fairbanks , Stephen Mark Whiteker , Richard Thomas Price , Matthew Bernard Buczek , Warren Rosal Ronk
发明人： Lee Alan Blanton , Gregory Joseph Meibers , Robert Paul Fairbanks , Stephen Mark Whiteker , Richard Thomas Price , Matthew Bernard Buczek , Warren Rosal Ronk
CPC分类号： B29C70/546 , B29C70/44 , B29C70/465 , B29L2031/7504 , F01D21/045 , F05D2300/614 , F05D2300/702 , Y02T50/672 , Y10T428/249928 , Y10T428/249933 , Y10T428/24994 , Y10T428/249944
摘要： A method for fabricating a reinforced matrix composite comprising the step of providing a composite preform having a fibrous structure and applying matrix material onto the preform in locations along the preform. A barrier material is applied to at least a portion of the coated preform to direct the flow of matrix material into the preform. The composite preform is heated to a temperature sufficient to render the matrix material viscous and insufficient to cure the matrix material. The pressure to the interior of the composite preform is reduced, while the pressure to the barrier material is increased. The temperature is maintained to flow the matrix material into the composite preform and to force gases from the fibrous structure. The composite preform is then cured and cooled to form a reinforced matrix composite having a low void content and a substantially uniform matrix distribution.
摘要翻译： 一种用于制造增强基质复合材料的方法，包括提供具有纤维结构的复合预型件并将基体材料施加到预制件上的预型件沿着预制件的位置的步骤。 将阻挡材料施加到涂覆预型件的至少一部分以将基体材料流引导到预成型件中。 将复合预制件加热到足以使基质材料粘稠并且不足以固化基质材料的温度。 对复合预制件内部的压力降低，同时对阻挡材料的压力增加。 保持温度以使基质材料流入复合预制件并迫使来自纤维结构的气体。 然后将复合预成型件固化并冷却以形成具有低空隙含量和基本均匀的基体分布的增强基质复合材料。
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公开(公告)号：US20090142496A1
公开(公告)日：2009-06-04
申请号：US11925331
申请日：2007-10-26
申请人： Lee Alan Blanton , Gregory Joseph Meibers , Robert Paul Fairbanks , Stephen Mark Whiteker , Richard Thomas Price , Matthew Bernard Buczek , Warren Rosal Ronk
发明人： Lee Alan Blanton , Gregory Joseph Meibers , Robert Paul Fairbanks , Stephen Mark Whiteker , Richard Thomas Price , Matthew Bernard Buczek , Warren Rosal Ronk
IPC分类号： B05D3/00
CPC分类号： B29C70/546 , B29C70/44 , B29C70/465 , B29L2031/7504 , F01D21/045 , F05D2300/614 , F05D2300/702 , Y02T50/672 , Y10T428/249928 , Y10T428/249933 , Y10T428/24994 , Y10T428/249944
摘要： A method for fabricating a reinforced matrix composite comprising the step of providing a composite preform having a fibrous structure and applying matrix material onto the preform in locations along the preform. A barrier material is applied to at least a portion of the coated preform to direct the flow of matrix material into the preform. The composite preform is heated to a temperature sufficient to render the matrix material viscous and insufficient to cure the matrix material. The pressure to the interior of the composite preform is reduced, while the pressure to the barrier material is increased. The temperature is maintained to flow the matrix material into the composite preform and to force gases from the fibrous structure. The composite preform is then cured and cooled to form a reinforced matrix composite having a low void content and a substantially uniform matrix distribution.
摘要翻译： 一种用于制造增强基质复合材料的方法，包括提供具有纤维结构的复合预型件并将基体材料施加到预制件上的预型件沿着预制件的位置的步骤。 将阻挡材料施加到涂覆预型件的至少一部分以将基体材料流引导到预成型件中。 将复合预制件加热到足以使基质材料粘稠并且不足以固化基质材料的温度。 对复合预制件内部的压力降低，同时对阻挡材料的压力增加。 保持温度以使基质材料流入复合预制件并迫使来自纤维结构的气体。 然后将复合预成型件固化并冷却以形成具有低空隙含量和基本均匀的基体分布的增强基质复合材料。
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10.发明申请Methods for fabricating composite structures with flanges having tethered corners 审中-公开用于制造具有带束缚角的凸缘的复合结构的方法公开(公告)号：US20080157418A1
公开(公告)日：2008-07-03
申请号：US11645975
申请日：2006-12-27
IPC分类号： B22F7/06
CPC分类号： B29C70/32 , B29C53/587 , B29C70/20 , B29C70/543 , B29K2105/0809 , B29K2105/101 , B29L2023/22 , B29L2031/7504
摘要： Methods for fabricating a composite structure with a flange having a tethered corner involving providing a composite structure forming tool including a first endplate and a second endplate and having a composite structure formed thereabout, applying at least one ply of barrier fibers about the composite structure adjacent to the first endplate of the composite structure forming tool, and wrapping at least one fiber tow about the barrier fibers.
摘要翻译： 一种用于制造具有带有连接角的凸缘的复合结构的方法，包括提供包括第一端板和第二端板的复合结构形成工具，并且在其周围形成复合结构，在复合结构周围施加至少一层屏障纤维， 复合结构形成工具的第一端板，并围绕阻挡纤维缠绕至少一根纤维丝束。
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