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公开(公告)号：US06691505B2
公开(公告)日：2004-02-17
申请号：US10046132
申请日：2002-01-09
IPC分类号： F02K900
CPC分类号： F02K9/974 , F02K9/346 , F05D2300/224 , F05D2300/43 , F05D2300/431 , F05D2300/603 , F05D2300/614 , F05D2300/615
摘要： Insulation for a rocket motor is provided, as is a method for insulating a rocket motor. The insulation includes a cured elastomer and vapor-grown carbon fibers dispersed in the cured elastomer. The cured elastomer is preferably formed from a precursor composition comprising an EPDM terpolymer. Generally, the vapor-grown carbon fibers have an internal graphitized tube surrounded by a sheath of vapor-deposited amorphous carbon.
摘要翻译： 提供火箭发动机的绝缘，绝热火箭发动机的方法也是如此。 绝缘体包括分散在固化的弹性体中的固化的弹性体和蒸气生长的碳纤维。 固化的弹性体优选由包含EPDM三元共聚物的前体组合物形成。 通常，气相生长碳纤维具有由气相沉积的无定形碳包裹的内部石墨化管。
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公开(公告)号：US06330792B2
公开(公告)日：2001-12-18
申请号：US09747979
申请日：2000-12-22
申请人： Charles S. Cornelius , Richard H. Counts , W. Neill Myers , Jeffrey D. Lackey , Warren Peters , Michael D. Shadoan , David L. Sparks , Timothy W. Lawrence
发明人： Charles S. Cornelius , Richard H. Counts , W. Neill Myers , Jeffrey D. Lackey , Warren Peters , Michael D. Shadoan , David L. Sparks , Timothy W. Lawrence
IPC分类号： F02K900
CPC分类号： F02K9/974 , B29C53/585 , B29L2031/3097 , F02K9/62 , F02K9/97 , Y10S60/909
摘要： A thrust chamber assembly for liquid fueled rocket engines and the method of making it wherein a two-piece mandrel wrapped with a silica tape saturated with a phenolic resin, the tape extending along the mandrel and covering the combustion chamber portion of the mandrel to the throat portion. The phenolic in the tape is cured and the end of the wrap is machined. The remainder of the mandrel is wrapped with a third silica tape. The resin in the third tape is cured and the assembly is machined. The entire assembly is then wrapped with a tow of graphite fibers wetted with an epoxy resin and, after the epoxy resin is cured, the graphite is machined to final dimensions.
摘要翻译： 用于液体燃料火箭发动机的推力室组件及其制造方法，其中包裹有用酚醛树脂饱和的二氧化硅胶带的两件式心轴，所述带沿心轴延伸并将心轴的燃烧室部分覆盖至喉部 一部分。 胶带中的酚醛固化，并且机器的末端被加工。 心轴的其余部分用第三个硅胶带包裹。 第三带中的树脂被固化并且组装被加工。 然后将整个组件用用环氧树脂润湿的石墨纤维丝束包裹，并且在环氧树脂固化之后，将石墨加工成最终尺寸。
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公开(公告)号：US06314719B1
公开(公告)日：2001-11-13
申请号：US09471540
申请日：1999-12-23
申请人： Jeffrey H. Hunt , Herbert R. Lander
发明人： Jeffrey H. Hunt , Herbert R. Lander
IPC分类号： F02K900
摘要： The ignition system includes an optical source capable of producing light having physical characteristics sufficient for optically driven chemical disassociation of a hydrogen peroxide oxidizer; and, an optical delivery system for providing optical delivery of light from the optical source to a combustion chamber. The ignition system is used for a propulsion producing engine having a combustion chamber for the introduction of a fuel and a hydrogen peroxide oxidizer. The initiation of combustion is produced by the non-linear, optical interaction of the produced light with a fuel and the oxidizer present in the combustion chamber, thereby leading to molecular disassociation of the oxidizer such that there is initiation of combustion.
摘要翻译： 点火系统包括能够产生足以使过氧化氢氧化剂的光学驱动化学分解的物理特性的光的光源; 以及用于提供从光源到燃烧室的光的光学传递的光学传送系统。 点火系统用于具有用于引入燃料和过氧化氢氧化剂的燃烧室的推进发动机。 通过产生的光与燃料和存在于燃烧室中的氧化剂的非线性光学相互作用产生燃烧的开始，从而导致氧化剂的分子分解，使得发生燃烧。
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公开(公告)号：US06314720B1
公开(公告)日：2001-11-13
申请号：US09490290
申请日：2000-01-19
IPC分类号： F02K900
CPC分类号： F02K9/62 , F02K9/974 , F05D2230/90 , F05D2300/2118 , F05D2300/611 , Y10T29/49346
摘要： A coating with the ability to protect (1) the inside wall (i.e., lining) of a rocket engine combustion chamber and (2) parts of other apparatuses that utilize or are exposed to combustive or high-temperature environments. The novelty of this invention lies in the manner a protective coating is embedded into the lining.
摘要翻译： 具有保护（1）火箭发动机燃烧室的内壁（即，衬里）的能力的涂层和（2）利用或暴露于可燃或高温环境的其它设备的部分。 本发明的新颖性在于保护性涂层嵌入衬里的方式。
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公开(公告)号：US06230491B1
公开(公告)日：2001-05-15
申请号：US09588384
申请日：2000-06-07
申请人： Kerry L. Wagaman
发明人： Kerry L. Wagaman
IPC分类号： F02K900
摘要： A family of water-based gas-generating liquid compositions is described. A composition of the present invention includes: hydrogen peroxide; ammonium nitrate; and water. Compositions of the present invention may be mixed with fuels to make monopropellants or used in bipropellant or hybrid systems. Alternative uses of the present invention include breathable gas generation.
摘要翻译： 描述了一系列水基气体产生液体组合物。 本发明的组合物包括：过氧化氢; 硝酸铵; 和水。 本发明的组合物可与燃料混合以制备单一推进剂或用于双组元推进剂或混合体系。 本发明的替代用途包括透气产生。
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公开(公告)号：US06170258B2
公开(公告)日：2001-01-09
申请号：US09391154
申请日：1999-09-08
申请人： Boris Ivanovich Katorgin , Vladimir Konstantinovich Chvanov , Felix Jurievich Chelkis , Vadim Lliich Semenov , Valentin Georgievich Polushin , Nina Ivanovna Murlykina
发明人： Boris Ivanovich Katorgin , Vladimir Konstantinovich Chvanov , Felix Jurievich Chelkis , Vadim Lliich Semenov , Valentin Georgievich Polushin , Nina Ivanovna Murlykina
IPC分类号： F02K900
CPC分类号： F02K9/60 , F02K9/42 , F05D2240/90
摘要： The liquid-propellant rocket engine comprises two combustion chambers, a gas generator, a turbopump assembly, pipelines as well as a frame having footpads and supports located in different planes that are perpendicular to the engine axis, said frame being made up of at least two welded rod sections. Said sections are fastened to each other by a plane rod joint. The engine pipelines are connected to the combustion chambers and comprise bellows balances or flexible hoses which have their movable ends connected directly to the combustion chambers or to pipes joined thereto. The frame is made demountable due to the use of threaded connections that joint together the frame sections and the plane rod joint. The frame is made as a compensation frame by placing the footpad plane over the support plane. A curved pipe joint comprises a curved pipe, a hinge and a frame. At its end on the outlet side, the pipe is provided with a balance for compensating angular displacements, for instance, a bellows balance with a cardan mechanism. The curved pipe is connected to the frame by a hinge, and its outlet end is gas-tightly connected to the bellows of the balance.
摘要翻译： 液体推进剂火箭发动机包括两个燃烧室，气体发生器，涡轮泵组件，管道以及位于垂直于发动机轴线的不同平面中的脚垫和支架的框架，所述框架由至少两个 焊接杆部分。 所述部分通过平面杆接头彼此紧固。 发动机管道连接到燃烧室，并且包括波纹管平衡或软管，其可动端部直接连接到燃烧室或连接到其上的管道。 由于使用将框架部分和平面杆接头连接在一起的螺纹连接，框架可拆卸。 通过将支脚平面放置在支撑平面上，框架作为补偿框架。 弯曲管接头包括弯管，铰链和框架。 在出口侧的端部，管道设置有用于补偿角位移的平衡，例如与万向节机构的波纹管平衡。 弯管通过铰链连接到框架，其出口端气密地连接到天平的波纹管。
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公开(公告)号：US06711890B2
公开(公告)日：2004-03-30
申请号：US10132950
申请日：2002-04-26
申请人： John R. McGuire
发明人： John R. McGuire
IPC分类号： F02K900
摘要： A pressure vessel is provided that includes first and second case segments mated with one another. First and second annular rubber layers are disposed inboard of the first and second case segments, respectively. The second annular rubber layer has a slot extending from the radial inner surface across a portion of its thickness to define a main body portion and a flexible portion. The flexible portion has an interfacing surface portion abutting against an interfacing surface portion of the first annular rubber layer to follow movement of the first annular rubber layer during operation of the pressure vessel. The slot receives pressurized gas and establishes a pressure-actuated joint between the interfacing surface portions. At least one of the interfacing surface portions has a plurality of enclosed and sealed recesses formed therein.
摘要翻译： 提供了包括彼此配合的第一和第二壳体段的压力容器。 第一和第二环形橡胶层分别设置在第一和第二壳段的内侧。 第二环形橡胶层具有从径向内表面穿过其厚度的一部分延伸的槽，以限定主体部分和柔性部分。 柔性部分具有邻接第一环形橡胶层的接合表面部分的接合表面部分，以在压力容器的操作期间跟随第一环形橡胶层的移动。 狭槽接收加压气体并且在接口表面部分之间建立压力致动接头。 接口表面部分中的至少一个具有形成在其中的多个封闭和密封的凹部。
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公开(公告)号：US06412274B1
公开(公告)日：2002-07-02
申请号：US09586057
申请日：2000-06-02
IPC分类号： F02K900
摘要： A modular solar thermal rocket that receives and absorbs solar energy and then acts as a heat exchanger to provide propulsive thrust. Thermal energy storage modules receive and store solar energy via thermal energy storage elements provided in each module. The solar energy is focused into a cavity defined by the modules by a solar energy secondary concentrator. A preheater is positioned adjacent the solar energy secondary concentrator and is in fluid communication with a propellant supply and one end of the thermal energy storage modules. A propulsion nozzle is in fluid communication with the opposite end of the thermal energy storage modules. Stored propellant is directed through the preheater and the thermal energy storage modules where it is heated to a high temperature. The propellant is then directed to the propulsion nozzle where it is exhausted into space to provide propulsive thrust.
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公开(公告)号：US06369409B1
公开(公告)日：2002-04-09
申请号：US08689867
申请日：1996-08-15
申请人： Hiroaki Takasu , Jun Osanai , Kenji Kitamura
发明人： Hiroaki Takasu , Jun Osanai , Kenji Kitamura
IPC分类号： F02K900
CPC分类号： H01L28/20 , H01L21/8221 , H01L21/84 , H01L27/0802 , H01L27/1203
摘要： It is an object to provide a highly precise bleeder resistance circuit having an accurate voltage division ratio and a small temperature coefficient of the resistance value and a highly precise semiconductor device having a small temperature coefficient using such a bleeder resistance circuit, e.g., a semiconductor device such as a voltage detector and a voltage regulator. Such characteristic features that the potential of electric conductors on the thin film resistors and electric conductors under the thin film resistors of a bleeder resistance circuit using thin film resistors is made almost equal to the potential of respective thin film resistors and that, when polysilicon is used in the thin film resistor, the dispersion of the resistance value is controlled and the temperature dependency of the resistance value is made lower by thinning the film thickness of the polysilicon thin film resistor are constituted.
摘要翻译： 本发明的目的是提供具有精确的分压比和较小的电阻值温度系数的高精度放电电阻电路，以及使用这种泄放电阻电路（例如半导体器件）具有较小温度系数的高精度半导体器件 例如电压检测器和电压调节器。 使用薄膜电阻器的泄放电阻电路的薄膜电阻器和薄膜电阻器下方的电导体的电位与各薄膜电阻器的电位几乎相等的特征在于，当使用多晶硅时 在薄膜电阻器中，控制电阻值的分散，并且通过使多晶硅薄膜电阻器的膜厚变薄来降低电阻值的温度依赖性。
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公开(公告)号：US06298659B1
公开(公告)日：2001-10-09
申请号：US09337457
申请日：1999-06-21
IPC分类号： F02K900
摘要： A vortex flow field and an apparatus and a method to produce and sustain it. The flow field includes an outer fluid vortex spiraling toward a closed end of the flow field generating apparatus and an inner fluid vortex substantially concentric with the outer vortex spiraling away from the closed end and toward an outlet opening in which the inner vortex spirals in the same direction as the outer vortex, but in the opposite axial direction. The invention also relates to a rocket propulsion system utilizing the flow field in which the propulsion system includes a combustion chamber with a fuel source and an oxidizer source flowing along the flow field.
摘要翻译： 涡流场，以及产生和维持它的装置和方法。 流场包括朝向流场发生装置的封闭端螺旋的外部流体涡流和与外部涡流基本上同心的内部流体涡流，该外部涡流远离封闭端螺旋形并且朝向出口开口，内部涡流在其中相同 方向作为外涡流，但在相反的轴向。 本发明还涉及利用流场的火箭推进系统，其中推进系统包括具有燃料源的燃烧室和沿流场流动的氧化剂源。
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