公开(公告)号：EP0335415A2

公开(公告)日：1989-10-04

申请号：EP89105704.4

申请日：1989-03-31

申请人： E.I. DU PONT DE NEMOURS AND COMPANY

发明人： Gupta, Dipak

IPC分类号： C08J5/24 ,  C08L79/08

CPC分类号： B32B5/12 ,  B29C35/0233 ,  B29C70/342 ,  B29K2079/08 ,  B29K2307/00 ,  B32B5/26 ,  B32B2260/021 ,  B32B2260/046 ,  B32B2262/106 ,  B32B2305/076 ,  B32B2305/08 ,  B32B2305/72 ,  B32B2605/18 ,  C08J5/24 ,  C08J2379/08 ,  Y10S264/78 ,  Y10T428/265 ,  Y10T428/30 ,  Y10T428/31721 ,  Y10T442/3902

摘要： Composite tooling of carbon fiber reinforced polyimide of high Tg is prepared by first curing in an autoclave followed by post-curing in an air circulating oven.

摘要翻译： 通过首先在高压釜中固化，然后在空气循环烘箱中后固化，制备高Tg的碳纤维增强聚酰亚胺的复合模具。

公开(公告)号：EP0270666A4

公开(公告)日：1989-07-26

申请号：EP87904751

申请日：1987-06-05

申请人： HYPERION CATALYSIS INT

发明人： TENNENT HOWARD G ,  BARBER JAMES J ,  HOCH ROBERT

IPC分类号： C08J5/04 ,  B01J27/20 ,  B01J35/06 ,  C01B31/02 ,  C03C14/00 ,  C04B14/38 ,  C04B35/622 ,  C04B35/80 ,  C08K7/06 ,  C22C49/00 ,  C30B29/62 ,  D01F9/12 ,  D01F9/127 ,  D01F11/12 ,  D04H1/42 ,  F16D69/02 ,  H01B1/02 ,  H01B1/04 ,  H01B1/16 ,  H01B1/18 ,  H01B1/24 ,  H01G9/048 ,  B32B9/00

CPC分类号： B82Y30/00 ,  B01J27/20 ,  B01J35/06 ,  B29K2307/00 ,  C04B14/386 ,  C04B35/62272 ,  C08K7/06 ,  D01F9/1272 ,  D01F9/1273 ,  D01F9/1275 ,  D01F9/1276 ,  D01F9/1277 ,  D01F9/1278 ,  D01F11/127 ,  F16D69/023 ,  H01B1/02 ,  H01B1/04 ,  H01B1/16 ,  H01B1/18 ,  H01B1/24

摘要： A discrete carbon fibril characterized by a substantially constant diameter between about 3.5 and about 70 nanometers, length greater than about 5 times the diameter and less than about 100 times the diameter, an outer region of multiple essentially continuous layers of ordered carbon atoms and a distinct inner core region. The invention further concerns a plurality of such fibrils. The fibrils of this invention may be produced by contacting for an appropriate period of time and at a suitable pressure a suitable metal-containing particle with a suitable gaseous, carbon-containing compound, at a temperature between about 850°C and 1200°C, or by treating discrete carbon fibrils, characterized by a length greater than about 100 times the diameter. Carbon fibrils may also be continuously produced by continuously contacting for an appropriate period of time at suitable conditions. Another aspect of the invention concerns a composition of matter comprising a carbon fiber or a carbon plate and a plurality of fibrils. Carbon fibrils and compositions of matter comprising carbon fibrils are useful in composites having a matrix of e.g., an organic polymer, an inorganic polymer or a metal. In specific embodiments, the fibrils or the compositions of matter may be used to reinforce a structural material, to enhance the electrical or thermal conductivity of a material, to increase the surface area of an electrode or capacitor plate, to provide a support for a catalyst, or to shield an object from electromagnetic radiation.

公开(公告)号：EP0312167A2

公开(公告)日：1989-04-19

申请号：EP88202256.9

申请日：1988-10-10

申请人： DSM N.V.

发明人： van de Kerke, Willem Jan

IPC分类号： B29C67/14 ,  B29C67/24 ,  B29C53/58

CPC分类号： C08J5/24 ,  B29C35/08 ,  B29C53/587 ,  B29C67/248 ,  B29C70/08 ,  B29C2035/0833 ,  B29K2067/06 ,  B29K2105/06 ,  B29K2105/24 ,  B29K2105/243 ,  B29K2277/00 ,  B29K2307/00 ,  B29K2309/08 ,  B29L2009/00 ,  C08J2367/06

摘要： The invention relates to a process for the production of a laminate structure comprising two cover layers based on unsaturated polyester and fibrous material sandwiching a layer with a relatively low density based on unsaturated polyester by applying the core layer to a first cover layer, and is characterized in that the core layer consists of fibrous material covered with a film of unsaturated polyester, the polyester being at least partially cured using a light sensitive initiator system, and then applying a second cover layer.

摘要翻译： 本发明涉及一种层压结构的制造方法，其包括基于不饱和聚酯和基于不饱和聚酯的具有相对低密度的层的纤维材料的两个覆盖层，其通过将芯层施加到第一覆盖层上而被表征 芯层由不饱和聚酯膜覆盖的纤维材料组成，聚酯使用光敏引发剂系统至少部分固化，然后施加第二覆盖层。

公开(公告)号：EP0136673A3

公开(公告)日：1986-05-14

申请号：EP84111627

申请日：1984-09-28

申请人： PHILLIPS PETROLEUM COMPANY

发明人： Still, Robert Dean, Jr. ,  Boeke, Paul John

IPC分类号： B29C67/14 ,  B29B15/12 ,  C08L81/02 ,  B32B15/14 ,  B32B05/00 ,  B29K81/00

CPC分类号： B32B38/08 ,  B29B15/12 ,  B29B15/125 ,  B29B15/127 ,  B29C70/50 ,  B29C2035/0855 ,  B29K2081/00 ,  B29K2081/04 ,  B29K2105/0064 ,  B29K2105/0854 ,  B29K2105/251 ,  B29K2277/10 ,  B29K2307/00 ,  B29K2309/08 ,  B29K2705/00 ,  B32B3/26 ,  B32B15/08 ,  B32B38/0008 ,  B32B2260/021 ,  B32B2260/046 ,  B32B2310/0868 ,  C08L9/06 ,  C08L25/10 ,  C08L81/02 ,  Y10T428/31533 ,  Y10T442/2902 ,  Y10T442/2984 ,  Y10T442/2992 ,  Y10T442/656

摘要： A method for preparing stampable composites of poly(arylene sulfide) compositions that are radio frequency energy sensitive and reinforced with fibrous or filamentous mat; the stampable composites prepared thereby; a method for preparing a laminate with metal sheet and fiber mat reinforced poly(arylene sulfide) in which the poly(arylene sulfide) is sensitive to radio frequency energy; a bonded laminate produced thereby; stamped objects produced from the composites and/or laminates.

公开(公告)号：EP0170353A1

公开(公告)日：1986-02-05

申请号：EP85303427.0

申请日：1985-05-15

申请人： HER MAJESTY THE QUEEN IN RIGHT OF CANADA AS REPRESENTED BY THE MINISTER OF NATIONAL DEFENCE

发明人： Gladstone, David H. ,  Robertson, William J. ,  Langlois, Raymond

IPC分类号： F41F17/04 ,  F41F3/048

CPC分类号： B29C53/805 ,  B29C70/207 ,  B29K2063/00 ,  B29K2307/00 ,  B29L2031/777 ,  F41A21/02

摘要： A barrel section (14) for a lightweight firearm (10) such as a recoilless gun which is subjected to extremely high transient internal pressures and temperatures on firing is formed from an epoxy-resin impregnated carbon fibre material. The material, in the form of an elongated tow (35) is wound on a mandrel (34), cured and then removed from the mandrel for subsequent operations such as machining and assembly. During manufacture, a gas-erosion preventing layer is formed on the mandrel and a plurality of layers of tow are helically-wound thereon at a helix angle
where a axial and Whoop are the axial and hoop stresses produced in the barrel section by axial and hoop loads respectively. Lightweight recoilless guns using barrels in accordance with the invention are lighter and less costly to fabricate than conventional guns and are capable of firing upwards of 30 rounds before excessive erosion causes the firearm to be unusable. This is in comparison to a capability of firing only 5 to 10 rounds before failure for conventional guns. Failure is usually the result of the high pressures and temperatures encountered during firing, upwards of 9,000 p.s.i. and 3,000°K.

公开(公告)号：EP0007149A1

公开(公告)日：1980-01-23

申请号：EP79300406.0

申请日：1979-03-14

申请人： THE BABCOCK & WILCOX COMPANY

发明人： Faverty, Delmar Allison ,  Shuck, Robert E.

IPC分类号： B29D3/02 ,  D04H1/60

CPC分类号： B29B15/105 ,  B29K2081/04 ,  B29K2307/00 ,  D04H1/60

摘要： To produce resin-impregnated fibres for use as a moulding composition for fibre-reinforced resin composites, a fibre tow (10) is chopped (12), fluidised and conveyed through a first flow-accelerating device (21) dispersed into a mixing chamber (30) where it is turbulently admixed with dry powdered resin injected into the chamber. The resin-impregnated fibres are withdrawn from the chamber (30) via a second flow-accelerating device (41) into a separating tank (50) in which the fluiding medium is separated from the resin-impregnated fibres.

摘要翻译： 为了制备树脂浸渍的纤维用作纤维增强树脂复合材料的模塑组合物，纤维丝束（10）短切（12），流化，并通过分散到混合腔的第一流动加速装置（21）传送（ 30）在那里与湍流注入腔室干粉状树脂混合。 树脂浸渍纤维由通过第二流加速装置（41）的室（30）抽入其中fluiding介质从浸渍有树脂的纤维中分离的分离罐（50）。

公开(公告)号：EP2155546B1

公开(公告)日：2018-11-28

申请号：EP08829152.1

申请日：2008-05-21

申请人： Raytheon Company

发明人： FACCIANO, Andrew B. ,  MOORE, Robert T. ,  SINNOCK, Kelly J. ,  CALDWELL, Scott T.

IPC分类号： B63H11/00 ,  B29C70/28 ,  B29L31/00 ,  B29K79/00 ,  B29K309/08 ,  F02K9/97 ,  B29K307/00

CPC分类号： F02K9/97 ,  B29C70/28 ,  B29K2079/08 ,  B29K2307/00 ,  B29K2309/08 ,  B29K2995/0015 ,  B29L2031/777 ,  F05D2300/2102 ,  F05D2300/211 ,  F05D2300/224 ,  F05D2300/434 ,  F05D2300/44 ,  F05D2300/603 ,  F05D2300/614

摘要： An integral composite rocket motor nozzle. The novel nozzle includes a first layer of a first reinforcement material, a second layer of a second reinforcement material, and a common matrix material surrounding the first and second reinforcement materials such that the reinforcement materials and matrix material form a single integral composite structure. In an illustrative embodiment, the first reinforcement material includes graphite fibers for providing structural support, and the second reinforcement material includes glass or quartz fibers for providing thermal insulation on a first side of the first layer. The nozzle may also include a third layer of a third reinforcement material for providing thermal insulation on a second side of the first layer. In a preferred embodiment, the first layer is shaped to form an integrated dome and nozzle structure.

公开(公告)号：EP2429801B1

公开(公告)日：2018-01-24

申请号：EP10728586.8

申请日：2010-05-12

申请人： Airbus Defence and Space GmbH

发明人： KUNTZ, Julian ,  STADLER, Franz

IPC分类号： B29C65/74 ,  B29C65/16

CPC分类号： B29C65/74 ,  B29B11/16 ,  B29C65/16 ,  B29C65/1635 ,  B29C65/1658 ,  B29C65/1683 ,  B29C66/1122 ,  B29C66/242 ,  B29C66/24244 ,  B29C66/43 ,  B29C66/721 ,  B29C66/7212 ,  B29C66/72141 ,  B29C66/729 ,  B29C66/7392 ,  B29C66/81267 ,  B29C66/81455 ,  B29C66/82661 ,  B29C66/836 ,  B29C66/8742 ,  B29C70/40 ,  B29C70/545 ,  B29K2105/06 ,  B29K2307/00 ,  B29K2313/00 ,  B29K2995/0027 ,  B29L2031/3076 ,  D06H5/00 ,  Y10T156/1054 ,  Y10T156/1062 ,  Y10T156/1082 ,  B29K2307/04

公开(公告)号：EP2440451A4

公开(公告)日：2017-12-20

申请号：EP09845908

申请日：2009-06-11

申请人： SAAB AB

发明人： HALLANDER PER ,  PETERSSON MIKAEL ,  WEIDMANN BJÖRN ,  GRANKÄLL TOMMY ,  STRINDBERG GÖTE ,  NORDIN PONTUS

IPC分类号： B64C1/00 ,  B29C65/48 ,  B29C65/52 ,  B64C3/20 ,  B64C3/26 ,  B64C7/00 ,  B82B1/00

CPC分类号： B64C1/00 ,  B29C65/4875 ,  B29C65/488 ,  B29C65/5057 ,  B29C66/112 ,  B29C66/131 ,  B29C66/543 ,  B29C66/71 ,  B29C66/721 ,  B29C66/7212 ,  B29C66/72141 ,  B29C66/72143 ,  B29C66/73711 ,  B29K2105/06 ,  B29K2105/167 ,  B29K2307/00 ,  B29L2031/3076 ,  B29L2031/3082 ,  B29L2031/3085 ,  B64C2001/0072 ,  B82Y30/00 ,  Y02T50/433 ,  Y10T428/24124 ,  Y10T428/24488 ,  Y10T428/249921 ,  Y10T428/31511 ,  B29K2307/04 ,  B29K2063/00

摘要： An aircraft structure including structural composite parts assembled together to form the aircraft structure. A bonding interlayer material bonds the structural composite parts to each other. The bonding interlayer material includes a nanostructure enhanced material. A method of producing an aircraft structure of assembled structural composite parts, being cured or semi-cured before assembly.

公开(公告)号：EP2440392B1

公开(公告)日：2017-10-25

申请号：EP09845906.8

申请日：2009-06-11

申请人： Saab AB

发明人： HALLANDER, Per ,  PETERSSON, Mikael ,  WEIDMANN, Björn ,  GRANKÄLL, Tommy ,  STRINDBERG, Göte ,  NORDIN, Pontus

IPC分类号： B29C70/14 ,  B29C65/00 ,  B64C1/06 ,  B29C65/02 ,  B29L31/30 ,  B29K105/24 ,  B29K105/16 ,  B29K105/06 ,  B29C70/46 ,  B29C35/02 ,  B29K307/00

CPC分类号： B64C1/06 ,  B29C35/02 ,  B29C65/02 ,  B29C66/112 ,  B29C66/1122 ,  B29C66/131 ,  B29C66/43441 ,  B29C66/49 ,  B29C66/496 ,  B29C66/71 ,  B29C66/721 ,  B29C66/7212 ,  B29C66/72141 ,  B29C66/73754 ,  B29C66/73941 ,  B29C70/14 ,  B29C70/46 ,  B29K2105/06 ,  B29K2105/167 ,  B29K2105/243 ,  B29K2307/00 ,  B29L2031/3076 ,  B29L2031/3082 ,  B29L2031/3085 ,  Y02T50/43 ,  Y10T428/24479 ,  B29K2307/04 ,  B29K2071/00 ,  B29K2067/00 ,  B29K2063/00 ,  B29K2031/00 ,  B29K2049/00 ,  B29K2061/04 ,  B29K2079/08 ,  B29K2081/04

摘要： A composite radius filler for use in an aircraft structure. The aircraft structure includes structural composite parts assembled together to form the aircraft structure. The composite radius filler is arranged between rounded sections of the structural composite parts for filling a gap formed between the structural composite parts. The composite radius filler is made structural by a nanostructure arranged within the composite radius filler for the reinforcement of the interface between the radius filler and the structural composite part. A method for producing an aircraft structure including a nano-reinforced radius filler.