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1. 发明申请

US20130323081A1 TURBOPUMP 有权
公开(公告)号：US20130323081A1
公开(公告)日：2013-12-05
申请号：US13904394
申请日：2013-05-29
申请人： SNECMA
发明人： Gaelle LE BOUAR , Richard PETIT
IPC分类号： F04D15/00
CPC分类号： F04D15/0066 , F02K9/48 , F02K9/563
摘要： The invention relates to a field of feeding reaction engines, and in particular a turbopump 9 for feeding at least one combustion chamber 2 with a first propellant, the turbopump comprising a pump 9a, a turbine 9b to the pump 9a in order to drive it, and a variable and/or disengageable braking device 11.
摘要翻译：本发明涉及进料反应发动机的领域，特别是用于将至少一个燃烧室2与第一推进剂一起供给的涡轮泵9，涡轮泵包括泵9a，向泵9a驱动的涡轮机9b，以及可变和/或可分离的制动装置11。

2. 发明申请

US20130247542A1 SPACE LAUNCHER PROPULSION SYSTEM IMPLEMENTING A METHOD OF REGULATING PROPELLANT COMPONENT CONSUMPTION 审中-公开
标题翻译：空间推进器推进系统实施调节推进组件消耗的方法
公开(公告)号：US20130247542A1
公开(公告)日：2013-09-26
申请号：US13823327
申请日：2011-09-20
申请人： Serge Le Gonidec
发明人： Serge Le Gonidec
IPC分类号： F02K9/00
CPC分类号： F02K9/00 , F01D17/085 , F02C9/30 , F02K9/563 , F02K9/96 , F05D2270/303
摘要： A space launcher propulsion system includes: an engine fed by at least two propellant component tanks; a measurement mechanism to measure a quantity of propellant component actually consumed in each of the tanks, by sensors becoming uncovered; an estimation mechanism to estimate instantaneous flow rates of each of the propellant components on the basis of at least one operating parameter of the engine; and a correction mechanism correcting the way the estimation mechanism estimates on the basis of the measured consumed quantities and of the estimated instantaneous flow rates.
摘要翻译：空间发射器推进系统包括：由至少两个推进剂组分罐供给的发动机; 一种测量机构，用于测量在每个罐中实际消耗的推进剂组分的数量，由传感器变得未被覆盖; 估计机构，用于基于发动机的至少一个操作参数估计每个推进剂部件的瞬时流量; 以及校正机构，其校正估计机构基于测量的消耗量和估计的瞬时流量估计的方式。

3. 发明授权

US07997060B2 Rocket engine power cycle 有权
标题翻译：火箭发动机动力循环
公开(公告)号：US07997060B2
公开(公告)日：2011-08-16
申请号：US11928204
申请日：2007-10-30
申请人： Christopher M. Erickson , James R. Lobitz , William R. Bissell , David E. Hanks , Corey D. Brown
发明人： Christopher M. Erickson , James R. Lobitz , William R. Bissell , David E. Hanks , Corey D. Brown
IPC分类号： F02K9/46
CPC分类号： F02K9/48 , F02K9/563
摘要： An expander heat exchanger cycle system provides a fuel or oxidizer routed through a heat exchanger to cool and condense a coolant/turbine drive fluid.
摘要翻译：膨胀器热交换器循环系统提供通过热交换器引导的燃料或氧化剂以冷却和冷凝冷却剂/涡轮机驱动流体。

4. 发明申请

US20040245406A1 MICROPUMP-BASED MICROTHRUSTER 失效
标题翻译：基于MICROPUMP的MICROTHRUSTER
公开(公告)号：US20040245406A1
公开(公告)日：2004-12-09
申请号：US10456722
申请日：2003-06-06
发明人： James V. Guiheen , Thirumalai G. Palanisamy
IPC分类号： B64G001/26
CPC分类号： F03H1/0012 , F02K9/46 , F02K9/563 , F02K9/605 , F04B43/043
摘要： A thruster for providing thrust for spacecraft positioning, which has a propellant reservoir for storing propellant, a reaction chamber for discharging a vapor for providing thrust, a pump module comprising one or more micropumps for drawing propellant from the reservoir and for systematically metering propellant to the reaction chamber in a controlled manner, and a controller for actuating the pump module.
摘要翻译：用于提供用于航天器定位的推力的推进器，其具有用于储存推进剂的推进剂储存器，用于排出用于提供推力的蒸气的反应室，包括一个或多个微型泵的泵模块，用于从储存器抽取推进剂并系统地将推进剂计量到反应室，以及用于致动泵模块的控制器。

5. 发明授权

US3161017A Liquid rocket thrust control 失效
标题翻译：液体火箭推力控制
公开(公告)号：US3161017A
公开(公告)日：1964-12-15
申请号：US82268859
申请日：1959-06-24
申请人： UNITED AIRCRAFT CORP
发明人： HOLMES TRENT H
IPC分类号： F02K9/56
CPC分类号： F02K9/563

6. 发明申请

US20110017873A1 DEVICE FOR POWERING THE PUMP OF A ROCKET ENGINE USING AN INERTIA WHEEL 有权
标题翻译：用于为动力轮驱动的发动机泵的装置
公开(公告)号：US20110017873A1
公开(公告)日：2011-01-27
申请号：US12681978
申请日：2008-10-03
申请人： Gerald Raymond
发明人： Gerald Raymond
IPC分类号： F02K9/46
CPC分类号： F02K9/563
摘要： An apparatus for driving a pump for fueling a rocket engine of a space vehicle. The apparatus comprises an inertia wheel and a transmitting device to transmit a rotation of the inertia wheel to the pump. The apparatus further comprises a measuring device to measure the rotation speed of the inertia wheel a clutching device to decouple the wheel and the pump for a speed lower than a pre-determined speed lower, which is lower than the nominal rotation speed of the wheel. The invention is particularly applicable to a space vehicle comprising a rocket engine wherein the fuel supply system comprises at least one pump driven by the apparatus of the invention and a starting device to start the apparatus while the space vehicle is in flight.
摘要翻译：一种用于驱动用于对空间车辆的火箭发动机进行加油的泵的装置。该装置包括惯性轮和传递装置，以将惯性轮的旋转传递到泵。该装置还包括测量装置，用于测量惯性轮的离合器的旋转速度，该离合器用于使车轮和泵的转速低于预定速度低于低于车轮的标称转速的预定速度。本发明特别适用于包括火箭发动机的空间飞行器，其中燃料供给系统包括由本发明的装置驱动的至少一个泵和用于在空中飞行器飞行时起动该装置的起动装置。

7. 发明申请

US20100252686A1 METHOD AND DEVICE ENABLING A ROCKET ENGINE PUMP TO BE DRIVEN BY AN INTERNAL COMBUSTION ENGINE 有权
标题翻译：使用内燃机驱动的发动机泵的方法和装置
公开(公告)号：US20100252686A1
公开(公告)日：2010-10-07
申请号：US12680608
申请日：2008-10-07
申请人： Gerald Raymond , Paul Caye , Frederic Richard
发明人： Gerald Raymond , Paul Caye , Frederic Richard
IPC分类号： F02K9/46
CPC分类号： F02K9/46 , F02K9/563
摘要： The subject of the invention is a device for driving a pump of a rocket engine of a space vehicle that comprises an air-breathing internal combustion engine running on an oxidizer/fuel mixture of the air/hydrocarbon type, wherein the supply of oxidant and fuel is provided by tanks and a circuit that are separate from the propellant tanks of the rocket engine. The invention applies to a device for fueling a rocket engine that includes at least two pumps, each driven by the device of the invention, and means for controlling the internal combustion engines for driving the pumps, adapted for independently varying the operating parameters of these engines so as to independently adjust the rotation speeds of the pumps.
摘要翻译：本发明的主题是用于驱动太空车辆的火箭发动机的泵的装置，其包括在空气/烃类型的氧化剂/燃料混合物上运行的空气呼吸内燃机，其中氧化剂和燃料的供应由坦克和与火箭发动机的推进剂罐分开的回路提供。本发明适用于一种用于加油火箭发动机的装置，该装置包括至少两个由本发明的装置驱动的泵，以及用于控制用于驱动泵的内燃机的装置，适于独立地改变这些发动机的运行参数以便独立地调节泵的转速。

8. 发明申请

US20100094522A1 METHOD AND A DEVICE FOR CALCULATING A STARTING OR STOP SEQUENCE FOR AN ENGINE 有权
标题翻译：用于计算发动机起动或停止序列的方法和装置
公开(公告)号：US20100094522A1
公开(公告)日：2010-04-15
申请号：US12578809
申请日：2009-10-14
申请人： Serge Le Gonidec
发明人： Serge Le Gonidec
IPC分类号： G06F19/00
CPC分类号： F02K9/56 , F02K9/563 , F02K9/94 , F02K9/95
摘要： The method serves to calculate a start sequence or a stop sequence for an engine, said sequence comprising a plurality of cues at which predetermined actions should be performed in the control of said engine. The method comprises: a step of obtaining at least one thermodynamic condition of said engine; and a step of calculating said sequence as a function of: said at least one thermodynamic condition; dimensional parameters of said engine; and criteria for proper operation of said engine.
摘要翻译：该方法用于计算发动机的起始序列或停止序列，所述序列包括多个提示，在所述多个提示中，在所述发动机的控制中应执行预定动作。该方法包括：获得所述发动机的至少一个热力学条件的步骤; 以及计算所述序列作为以下功能的步骤：所述至少一个热力学条件; 所述发动机的尺寸参数; 以及用于正确操作所述发动机的标准。

9. 发明授权

US06892525B2 Micropump-based microthruster 失效
标题翻译：微型微型推力器
公开(公告)号：US06892525B2
公开(公告)日：2005-05-17
申请号：US10456722
申请日：2003-06-06
申请人： James V. Guiheen , Thirumalai G. Palanisamy
发明人： James V. Guiheen , Thirumalai G. Palanisamy
IPC分类号： F02K9/46 , F02K9/56 , F02K9/60 , F03H1/00 , F03H99/00 , F04B43/04 , F02K9/42
CPC分类号： F03H1/0012 , F02K9/46 , F02K9/563 , F02K9/605 , F04B43/043
摘要： A thruster for providing thrust for spacecraft positioning, which has a propellant reservoir for storing propellant, a reaction chamber for discharging a vapor for providing thrust, a pump module comprising one or more micropumps for drawing propellant from the reservoir and for systematically metering propellant to the reaction chamber in a controlled manner, and a controller for actuating the pump module.
摘要翻译：用于提供用于航天器定位的推力的推进器，其具有用于储存推进剂的推进剂储存器，用于排出用于提供推力的蒸气的反应室，包括一个或多个微型泵的泵模块，用于从储存器抽取推进剂并系统地将推进剂计量到反应室，以及用于致动泵模块的控制器。

10. 发明申请

US20030136111A1 Hybrid rocket motor using a turbopump to pressurize a liquid propellant constituent 失效
标题翻译：混合式火箭发动机使用涡轮泵对液体推进剂成分进行加压
公开(公告)号：US20030136111A1
公开(公告)日：2003-07-24
申请号：US10054646
申请日：2002-01-22
申请人： HY PAT CORPORATION
发明人： Korey R. Kline , Kevin W. Smith , Eric E. Schmidt , Thomas O. Bales
IPC分类号： F02K009/72
CPC分类号： F02K9/72 , F02K9/46 , F02K9/48 , F02K9/50 , F02K9/563
摘要： A hybrid rocket motor includes a storage tank which stores an oxidizer under relatively low pressure, a turbopump preferably directly coupled to an outlet of the storage tank which pressurizes the oxidizer to a relatively high pressure, a combustion chamber including a solid fuel, and an injector between the turbopump and combustion chamber through which the oxidizer is injected into the combustion chamber. According to a preferred aspect of the invention, the turbopump is operated by an expander cycle of a heat exchanger. According to another preferred aspect of the invention, the fluid flowing through the heat exchanger is oxidizer tapped from the storage tank. A barrier is maintained between an oxidizer feed line from the turbopump and the injector until sufficient pressure is created by the turbopump to pump the oxidizer at the requisite pressure into the injector.
摘要翻译：混合式火箭发动机包括储存在相对较低压力下的氧化剂的储罐，优选直接耦合到存储罐出口的涡轮泵，其将氧化剂加压到相对较高的压力，包括固体燃料的燃烧室和喷射器在涡轮泵和燃烧室之间，氧化剂通过燃烧室注入燃烧室。根据本发明的优选方面，涡轮泵由热交换器的膨胀机循环来操作。根据本发明的另一个优选方面，流过热交换器的流体是从储罐中抽出的氧化剂。在涡轮泵和注射器的氧化剂进料管线之间保持屏障，直到由涡轮泵产生足够的压力以将氧化剂以必要的压力泵入喷射器。

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