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11. 发明申请

US20030136109A1 Hybrid rocket motor using a turbopump to pressurize a liquid propellant constituent 失效
公开(公告)号：US20030136109A1
公开(公告)日：2003-07-24
申请号：US10054080
申请日：2002-01-22
申请人： HY PAT CORPORATION
发明人： Korey R. Kline , Kevin W. Smith , Thomas O. Bales
IPC分类号： F02K009/72
CPC分类号： F02K9/563 , F02K9/46 , F02K9/48 , F02K9/72 , F04D13/043
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.

12. 发明授权

US4541238A Process for the control of the mixture ratio of fuel and oxidizer for a liquid fuel motor by measuring flows, and control systems for carrying out this process 失效
标题翻译：用于通过测量流量来控制液体燃料电动机的燃料和氧化剂的混合比的方法以及用于执行该过程的控制系统
公开(公告)号：US4541238A
公开(公告)日：1985-09-17
申请号：US482406
申请日：1983-04-06
申请人： Alfred K. Scheller
发明人： Alfred K. Scheller
IPC分类号： F02K9/56 , F02K9/48
CPC分类号： F02K9/563
摘要： The process comprises the comparison of the flows of fuel and oxidizer measured at the outlet of the turbopumps with a set value corresponding to the optimum value of the mixture. The set value is periodically modified in dependence on the volumes of fuel and oxidizer remaining in the tanks. The control system for carrying out the process comprises a control valve controlled by an electronic device processing the measurements and disposed in a fuel or oxidizer supply pipe of a driving gas generator for the turbine of a turbopump or in the gas supply pipe of a turbopump, or disposed between the two pipes supplying the same fuel or oxidizer two driving gas generators, or between the gas outlets of the two turbines of the turbopumps.
摘要翻译：该方法包括在涡轮泵的出口处测量的燃料和氧化剂的流量与对应于混合物的最佳值的设定值的比较。根据储罐中剩余的燃料和氧化剂的体积，周期性地修改设定值。用于执行该过程的控制系统包括由处理测量值的电子设备控制的控制阀，并且设置在用于涡轮泵的涡轮机或涡轮泵的气体供给管的驱动气体发生器的燃料或氧化剂供应管中，或设置在供应相同燃料或氧化剂两个驱动气体发生器的两个管之间，或者在涡轮泵的两个涡轮机的气体出口之间。

13. 发明授权

US11649786B2 Hybrid rocket engine using electric motor-driven oxidizer pump 有权
公开(公告)号：US11649786B2
公开(公告)日：2023-05-16
申请号：US17293127
申请日：2019-11-19
申请人： INNOSPACE CO., LTD.
发明人： Soo Jong Kim , Sung Bong Cho , Keun Hwan Moon , Sung Hoon Ryu
IPC分类号： F02K9/44 , F02K9/08 , F02K9/46 , F02K9/50 , F02K9/56 , F02K9/72
CPC分类号： F02K9/44 , F02K9/08 , F02K9/46 , F02K9/50 , F02K9/563 , F02K9/72 , F05D2260/213
摘要： Proposed is a hybrid rocket engine using an electric motor-driven oxidizer pump, the hybrid rocket engine including: an oxidizer tank configured to store the oxidizer; an oxidizer pump configured to pressurize the oxidizer by being connected to the oxidizer tank through a first oxidizer supply line; a drive unit including an electric motor configured to drive the oxidizer pump and a battery configured to supply power to the electric motor; an auxiliary oxidizer line configured to guide the oxidizer from the oxidizer tank to the electric motor to cool the electric motor; an oxidizer recirculation line configured to recharge oxidizer vapor, generated through heat exchange between the electric motor and the oxidizer, to the oxidizer tank, thereby pressurizing an inner side of the oxidizer tank; and a combustion chamber configured to combust the oxidizer and fuel by being connected to the oxidizer pump through a second oxidizer supply line.

14. 发明授权

US08632319B2 Device for powering the pump of a rocket engine using an inertia wheel 有权
标题翻译：使用惯性轮为火箭发动机的泵供电的装置
公开(公告)号：US08632319B2
公开(公告)日：2014-01-21
申请号：US12681978
申请日：2008-10-03
申请人： Gerald Raymond
发明人： Gerald Raymond
IPC分类号： F04B49/00 , F04B23/08 , F04B9/14
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。

15. 发明授权

US08430361B2 Method and device enabling a rocket engine pump to be driven by an internal combustion engine 有权
标题翻译：能够使内燃机驱动火箭发动机泵的方法和装置
公开(公告)号：US08430361B2
公开(公告)日：2013-04-30
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： B64G1/40
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。

16. 发明授权

US06640536B2 Hybrid rocket motor using a turbopump to pressurize a liquid propellant constituent 失效
公开(公告)号：US06640536B2
公开(公告)日：2003-11-04
申请号：US10054646
申请日：2002-01-22
申请人： Korey R. Kline , Kevin W. Smith , Eric E. Schmidt , Thomas O. Bales
发明人： Korey R. Kline , Kevin W. Smith , Eric E. Schmidt , Thomas O. Bales
IPC分类号： C06D500
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.

17. 发明授权

US3224189A Liquid rocket propellant feed system 失效
标题翻译：液体火箭推进剂进料系统
公开(公告)号：US3224189A
公开(公告)日：1965-12-21
申请号：US28455363
申请日：1963-05-31
申请人： MARTIN MARIETTA CORP
发明人： KENNY RICHARD J
IPC分类号： B64G1/40 , F02K9/56
CPC分类号： B64G1/402 , B64G1/401 , F02K9/563

18. 发明授权

US3204402A Step function thrust control 失效
标题翻译：阶梯功能推力控制
公开(公告)号：US3204402A
公开(公告)日：1965-09-07
申请号：US6977160
申请日：1960-11-16
申请人： UNITED AIRCRAFT CORP
发明人： HOLMES TRENT H
IPC分类号： F02K9/56
CPC分类号： F02K9/563

19. 发明授权

US3094838A Thrust control system 失效
标题翻译：推力控制系统
公开(公告)号：US3094838A
公开(公告)日：1963-06-25
申请号：US82106859
申请日：1959-06-17
申请人： UNITED AIRCRAFT CORP
发明人： EVANS FREDERICK P
IPC分类号： F02K9/56
CPC分类号： F02K9/563

20. 发明授权

US3040522A Rocket engine control system 失效
标题翻译：火箭发动机控制系统
公开(公告)号：US3040522A
公开(公告)日：1962-06-26
申请号：US76059958
申请日：1958-09-12
申请人： BENDIX CORP
发明人： WILLIAMSON JOHN R , HAWK CARL D
IPC分类号： F02K9/56
CPC分类号： F02K9/563

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