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1. 发明授权

US5380475A Process for manufacturing an oxidation-stable component on a CFC base, particularly for space travel 失效
标题翻译：在CFC基础上制造氧化稳定组分的方法，特别是用于太空旅行
公开(公告)号：US5380475A
公开(公告)日：1995-01-10
申请号：US973376
申请日：1992-11-09
申请人： Peter Goedtke , Ernst Blenninger , Manfred Lechner , Ulrich Papenburg , Peter Sindlhauser , Ulrich Goetz
发明人： Peter Goedtke , Ernst Blenninger , Manfred Lechner , Ulrich Papenburg , Peter Sindlhauser , Ulrich Goetz
IPC分类号： C04B35/573 , F02K9/97 , C04B35/52 , C08K7/06
CPC分类号： C04B35/573 , F02K9/974 , Y10T428/30
摘要： For the manufacturing of an oxidation-stable component that can withstand temperature changes for space travel, a solid CFC-body with a density of from 0.1 to 0.8 g/cm.sup.3, which has nondirectional short fibers, is made from short carbon fibers and a hardenable resin binder. From the solid CFC-body, a CFC-blank having the dimensions of the component to be manufactured is prepared by means of turning or other material cutting. The CFC-blank is infiltrated with pyrolytic carbon to a density of no more than 1.0 g/cm.sup.3 and then with metallic silicon so that its density amounts to more than 2.0 g/cm.sup.3. A portion of the metallic silicon is reacted with the pyrolytic carbon to form silicon carbide. The proportion of the unreacted metallic silicon which remains in the component after this reaction amounts to at least 15 percent by weight.
摘要翻译：对于可以承受空间行进温度变化的氧化稳定组分的制造，具有非定向短纤维的密度为0.1至0.8g / cm 3的固体CFC体由短碳纤维和可硬化的树脂粘合剂。通过固体CFC体，通过车削或其他材料切割来制备具有要制造的部件的尺寸的CFC坯料。 CFC-坯料用热解碳渗透至不超过1.0g / cm 3的密度，然后用金属硅渗透，使其密度达到2.0g / cm3以上。一部分金属硅与热解碳反应形成碳化硅。在该反应后残留在组分中的未反应的金属硅的比例等于至少15重量％。

2. 发明授权

US5505805A Method for the production of reflectors 失效
标题翻译：反射器的生产方法
公开(公告)号：US5505805A
公开(公告)日：1996-04-09
申请号：US25145
申请日：1993-03-02
申请人： Ulrich Papenburg , Peter Goedtke , Ernst Blenninger
发明人： Ulrich Papenburg , Peter Goedtke , Ernst Blenninger
IPC分类号： C04B37/00 , G02B5/08 , G02B7/182 , G02B7/183 , B32B31/06 , B32B31/12 , B32B31/26
CPC分类号： G02B7/183 , C04B35/63476 , C04B35/6455 , C04B37/001 , C04B37/003 , C04B37/008 , G02B5/08 , C04B2235/6562 , C04B2235/6567 , C04B2235/658 , C04B2237/083 , C04B2237/121 , C04B2237/125 , C04B2237/16 , C04B2237/30 , C04B2237/365 , C04B2237/52 , C04B2237/60 , C04B2237/61 , C04B2237/64 , C04B2237/70 , C04B2237/704 , C04B2237/72 , C04B2237/76 , Y10S359/90 , Y10T156/10
摘要： For the production of lightweight reflectors or mirror structures, metallic silicon of sufficient thickness is applied to a CFC or CMC substrate preform structure having the dimensions of the component to be produced by a heat treatment process, in particular at temperatures between 1300.degree. C. and 1600.degree. C. and in a vacuum or in a protective atmosphere. In this way, reflectors or mirror structures are formed directly. It is possible to work at temperatures of 300.degree.-600.degree. C. when the silicon is applied in the form of wafers which are joined to the substrate preform by way a zone of a melt eutectic incorporating a nonferrous metal. Preferably the nonferrous metal is gold.
摘要翻译：为了生产轻型反射镜或镜面结构，将具有足够厚度的金属硅施加到具有通过热处理工艺制造的部件的尺寸的CFC或CMC基材预成型件结构，特别是在1300℃和 1600℃，并在真空或保护气氛中。以这种方式，直接形成反射镜或反射镜结构。当硅以晶片的形式施加时，可以在300-600℃的温度下工作，所述晶片通过掺入有色金属的熔融共晶区连接到基底预制件。优选地，有色金属是金。

3. 发明授权

US5565052A Method for the production of a reflector 失效
标题翻译：反射器的制造方法
公开(公告)号：US5565052A
公开(公告)日：1996-10-15
申请号：US300633
申请日：1994-09-02
申请人： Ulrich Papenburg , Ernst Blenninger , Peter Goedtke , Michael Deyerler
发明人： Ulrich Papenburg , Ernst Blenninger , Peter Goedtke , Michael Deyerler
IPC分类号： C04B37/00 , C04B41/50 , C04B41/52 , C04B41/85 , C04B41/89 , G02B5/08 , G02B7/182 , G02B7/183 , B32B31/12 , B32B31/26
CPC分类号： G02B7/183 , C04B35/65 , C04B37/001 , C04B41/5096 , C04B41/52 , C04B41/85 , C04B41/89 , G02B5/08 , C04B2237/34 , C04B2237/365 , C04B2237/407 , C04B2237/52 , C04B2237/586 , Y10S359/90 , Y10T156/1064
摘要： In order to produce lightweight mirror structures or other reflecting components, preformed silicon elements of sufficient wall thickness are applied to a CFC or CMC substrate structure with the dimensions of the component to be produced, at a temperature in the range 1300.degree. C. and 1600.degree. C. either in vacuum or in a protective atmosphere. In this way a mirror structure or reflector is formed directly. It is possible to work at temperatures in the range of 300.degree. C. to 600.degree. C. when the silicon is applied in the form of a preform such as a wafer, which is joined to the substrate by way of a zone of a melt eutectic incorporating a nonferrous metal, which is preferably gold. The surfaces are subsequently coated.
摘要翻译：为了生产轻质镜面结构或其他反射部件，将具有足够壁厚的预制硅元件在1300℃和1600℃的温度下施加到要生产的部件的尺寸的CFC或CMC基板结构在真空中或在保护气氛中。以这种方式直接形成镜面结构或反射镜。当硅以诸如晶片的预成型体的形式施加时，可以在300℃至600℃的温度下工作，该晶片通过熔融区连接到基底共晶合并有色金属，优选为金。随后涂覆表面。

4. 发明授权

US5825565A Reflector 失效
标题翻译：反射器
公开(公告)号：US5825565A
公开(公告)日：1998-10-20
申请号：US653334
申请日：1996-05-24
申请人： Ulrich Papenburg , Ernst Blenninger , Peter Goedtke , Michael Deyerler
发明人： Ulrich Papenburg , Ernst Blenninger , Peter Goedtke , Michael Deyerler
IPC分类号： C04B37/00 , C04B41/50 , C04B41/52 , C04B41/85 , C04B41/89 , G02B5/08 , G02B7/182 , G02B7/183 , G02B1/10
CPC分类号： G02B7/183 , C04B35/65 , C04B37/001 , C04B41/5096 , C04B41/52 , C04B41/85 , C04B41/89 , G02B5/08 , C04B2237/34 , C04B2237/365 , C04B2237/407 , C04B2237/52 , C04B2237/586 , Y10S359/90 , Y10T156/1064
摘要： In order to produce lightweight mirror structures or other reflecting components, preformed silicon elements of sufficient wall thickness are applied to a CFC or CMC substrate structure with the dimensions of the component to be produced, at a temperature in the range 1300.degree. C. and 1600.degree. C. either in vacuum or in a protective atmosphere. In this way a mirror structure or reflector is formed directly. It is possible to work at temperatures in the range of 300.degree. C. to 600.degree. C. when the silicon is applied in the form of a preform such as a wafer, which is joined to the substrate by way of a zone of a melt eutectic incorporating a nonferrous metal, which is preferably gold. The surfaces are subsequently coated.
摘要翻译：为了生产轻质镜面结构或其他反射部件，将具有足够壁厚的预制硅元件在1300℃和1600℃的温度下施加到要生产的部件的尺寸的CFC或CMC基板结构在真空中或在保护气氛中。以这种方式直接形成镜面结构或反射镜。当硅以诸如晶片的预成型体的形式施加时，可以在300℃至600℃的温度下工作，该晶片通过熔融区连接到基底共晶合并有色金属，优选为金。随后涂覆表面。

5. 发明授权

US06389801B1 Jet propulsion power unit with non-metal components 失效
标题翻译：具有非金属部件的喷气推进动力装置
公开(公告)号：US06389801B1
公开(公告)日：2002-05-21
申请号：US09459285
申请日：1999-12-17
申请人： Ulrich Papenburg , Ernst Blenninger , Henning Herbig , Guenter Langel
发明人： Ulrich Papenburg , Ernst Blenninger , Henning Herbig , Guenter Langel
IPC分类号： F02K900
CPC分类号： F23R3/007 , F02K9/97 , F02K9/972 , F02K9/974 , F05D2300/224 , F23M2900/05004
摘要： A rocket engine has a combustion chamber and an expansion chamber interconnected by a nozzle. Both chambers and the nozzle are made of carbon fiber reinforced silicon carbide formed as a monolithic rocket engine body or formed in sections bonded to each other to also form such a monolithic rocket engine body. The rocket engine body is mounted in a support structure, preferably made of a metal. The rocket engine body sections are produced by mechanical machining of respective blanks made of C/SiC materials. Cooling channels and/or heat insulation structures are used for heat control. The insulation structures are preferably also made of C/SiC materials or of carbon fiber felts or of graphite film.
摘要翻译：火箭发动机具有通过喷嘴相互连接的燃烧室和膨胀室。两个腔室和喷嘴由碳纤维增强的碳化硅制成，形成为整体式火箭发动机体，或者形成为彼此结合的部分，也形成这种整体式火箭发动机体。火箭发动机主体安装在优选由金属制成的支撑结构中。火箭发动机主体部分通过机械加工由C / SiC材料制成的各坯料制成。冷却通道和/或隔热结构用于热控制。绝缘结构优选也由C / SiC材料或碳纤维毡或石墨膜制成。

6. 发明授权

US06460807B1 Missile components made of fiber-reinforced ceramics 失效
标题翻译：由纤维增强陶瓷制成的导弹部件
公开(公告)号：US06460807B1
公开(公告)日：2002-10-08
申请号：US09242372
申请日：1999-12-10
申请人： Manfred Braitinger , Manfred Selzer , Ulrich Papenburg
发明人： Manfred Braitinger , Manfred Selzer , Ulrich Papenburg
IPC分类号： B32B527
CPC分类号： F42B15/34 , F42B12/72
摘要： The missile comprises a nose, fixed fins or movable fins, gas rudders, propelling nozzles and blast pipe inserts, combustion chamber liners, tail cone, grid fins, fluid elements and radome or subcomponents of these made of carbon fiber-reinforced silicon carbide (C/SiC) and/or carbon fiber-reinforced carbon (C/C) and/or silicon carbide fiber-reinforced silicon carbide (SiC/SiC) which are integrated in a missile structure. The missile components may be made of C/SiC and/or C/C and/or SiC/SiC with continuous fiber reinforcement and/or chopped fiber reinforcement or combinations thereof. The missile components may be prepared by mechanical machining of C/SiC and/or C/C and/or SiC/SiC blanks either in a single piece or by co-infiltration with carbon or silicon or silicon carbide and/or co-siliconizing of separate C/SiC and/or C/C and/or SiC/SiC segments to result in a monolithic structure. Cooling of the missile components may be achieved by providing cooling ducts and/or recesses in the C/SiC and/or C/C structure and/or the SiC/SiC structure and/or by means of insulating materials such as carbon fiber felts or C/SiC or C/C or SiC/SiC or graphite sheets or combinations thereof.
摘要翻译：导弹包括由碳纤维增强碳化硅（C）制成的鼻子，固定翅片或活动翅片，气舵，推进喷嘴和鼓风管插件，燃烧室衬垫，尾锥，网格翅片，流体元件和天线罩或子部件 / SiC）和/或碳纤维增强碳（C / C）和/或集成在导弹结构中的碳化硅纤维增强碳化硅（SiC / SiC）。导弹部件可以由C / SiC和/或C / C和/或具有连续纤维增强和/或短切纤维增强件或其组合的SiC / SiC制成。导弹部件可以通过以单个部件机械加工C / SiC和/或C / C和/或SiC / SiC坯料或通过与碳或硅或碳化硅的共渗和/或/ 分离的C / SiC和/或C / C和/或SiC / SiC段以产生整体结构。导弹部件的冷却可以通过在C / SiC和/或C / C结构和/或SiC / SiC结构中提供冷却管道和/或凹槽，和/或通过绝缘材料如碳纤维毡或 C / SiC或C / C或SiC / SiC或石墨片或其组合。

7. 发明申请

US20090230241A1 Device for Fastening an Object 审中-公开
标题翻译：用于固定对象的设备
公开(公告)号：US20090230241A1
公开(公告)日：2009-09-17
申请号：US12227336
申请日：2007-05-16
申请人： Christian Heller , Ulrich Papenburg
发明人： Christian Heller , Ulrich Papenburg
IPC分类号： B64C1/20
CPC分类号： B64D9/003 , B60P7/0815 , B64C1/20
摘要： The invention relates to a device for immobilizing an object on an anchor point, a rail or the like, inside a space, especially a cargo hold or passenger compartment of a helicopter. According to the invention, a detachable connecting element is interposed between the anchor point or the rail and the object.
摘要翻译：本发明涉及一种用于将物体固定在锚点，轨道等上的装置，在空间内，特别是直升机的货舱或乘客舱内。根据本发明，可拆卸连接元件插入在锚点或轨道与物体之间。

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