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21. 发明授权

US2984968A Automatic control of oxidizer and fuel turbopump system for a rocket engine 失效
标题翻译：自动控制火箭发动机的氧化剂和燃料涡轮泵系统
公开(公告)号：US2984968A
公开(公告)日：1961-05-23
申请号：US36310853
申请日：1953-06-22
申请人： NORTH AMERICAN AVIATION INC
发明人： HUNTER JR WILLIAM C , MOWER WILLIAM W , SUTTON GEORGE P , MORRIS JAMES P , NEWTON JOHANNES S
IPC分类号： F02K9/48 , F02K9/56
CPC分类号： F02K9/563 , F02K9/48

22. 发明授权

US12006894B1 Jettisonable battery systems for powering electrical turbopumps for launch vehicle rocket engine systems 有权
公开(公告)号：US12006894B1
公开(公告)日：2024-06-11
申请号：US17818232
申请日：2022-08-08
申请人： Rocket Lab USA, Inc.
发明人： Peter Joseph Beck , Naomi Altman , Jarrod William Burton , Shaun Keith O'Donnell
IPC分类号： F02K9/46 , F02K99/00 , H01M6/50 , H01M8/18 , H01M8/20 , F02K9/56
CPC分类号： F02K9/46 , F02K99/00 , H01M6/5044 , H01M8/188 , H01M8/20 , F02K9/563 , H01M2220/20
摘要： A launch vehicle having one or more rocket engines, an electric turbopump, and a plurality of batter units. Subsets of the battery units are jettisonable from the launch vehicle using battery jettison mechanisms. The launch vehicle may also include a controller that may determine that a remaining battery capacity of a first proper subset of the battery units is no longer needed for the remaining duration of a flight of the launch vehicle and may then, responsive to such a determination, cause the first proper subset of the battery units to be jettisoned.

23. 发明申请

US20160319772A1 METHOD FOR CONTROLLING A PROPULSION SYSTEM 审中-公开
标题翻译：控制推进系统的方法
公开(公告)号：US20160319772A1
公开(公告)日：2016-11-03
申请号：US15107700
申请日：2014-12-30
申请人： SNECMA
发明人： Gaëlle LE BOUAR
IPC分类号： F02K9/58 , F02K9/48
CPC分类号： F02K9/58 , F02K9/48 , F02K9/563 , F05D2270/304 , F05D2270/3061
摘要： The invention relates to the field of propulsion assemblies, and in particular to rocket engines of the “expander” type, wherein at least one propulsion chamber (40) is fed with at least a first propellant by a first pump (33) coupled to a first turbine (34) that is driven by partial expansion of said first propellant upstream from said propulsion chamber (40) after passing, downstream from the first pump (33), through a heat exchanger (23) heated by said propulsion chamber (40). A method of the invention for controlling such a propulsion assembly (10) comprises the steps of determining whether there exists a risk of instability for the propulsion assembly (10), and in response to determining that said risk of instability exists, using a branch connection (28) situated between the first turbine (34) and the propulsion chamber (40) to shed a portion of said first propellant.
摘要翻译：本发明涉及推进组件领域，特别涉及“膨胀机”类型的火箭发动机，其中至少一个推进室（40）由第一泵（33）供给至少第一推进剂，第一泵（33）第一涡轮机（34），其在所述推进室（40）的上游在所述第一泵（33）的下游经过由所述推进室（40）加热的热交换器（23）经过所述第一推进剂的部分膨胀之后被驱动，。用于控制这种推进组件（10）的本发明的方法包括以下步骤：确定是否存在用于推进组件（10）的不稳定性的风险，并且响应于确定存在所述不稳定性的风险，使用分支连接（28）位于所述第一涡轮（34）和所述推进室（40）之间以使所述第一推进剂的一部分脱落。

24. 发明申请

US20160312652A1 PASSIVE OVERSPEED CONTROLLED TURBO PUMP ASSEMBLY 审中-公开
标题翻译：被动超控式涡轮泵组件
公开(公告)号：US20160312652A1
公开(公告)日：2016-10-27
申请号：US14695079
申请日：2015-04-24
申请人： Hamilton Sundstrand Corporation
发明人： Richard A. Himmelmann
IPC分类号： F01D21/02 , F01D5/02 , F01D15/08 , F01D9/02 , F01D15/10 , F04D17/08 , F01D17/20
CPC分类号： F01D21/02 , F01D5/02 , F01D9/02 , F01D15/08 , F01D15/10 , F01D17/20 , F01D17/205 , F02K9/48 , F02K9/563 , F02K9/805 , F02K9/84 , F04D17/08 , F04D27/0261 , F05D2210/12 , F05D2220/30 , F05D2220/768 , F05D2240/128 , F05D2240/24 , F05D2260/406 , F05D2270/021 , F05D2270/42 , F05D2270/64
摘要： A turbine pump assembly has a turbine, a centrifugal pump, and a passive electrical speed control system. The turbine has a peak efficiency at a first speed that is lower than a second speed at which the centrifugal pump is operating at a peak power requirement. A rocket thrust vector control system is also disclosed.
摘要翻译：涡轮泵组件具有涡轮机，离心泵和无源电速度控制系统。涡轮机的第一速度的峰值效率低于离心泵在峰值功率要求下运行的第二速度。还公开了一种火箭推力矢量控制系统。

25. 发明授权

US09194333B2 Turbopump 有权
标题翻译：涡轮泵
公开(公告)号：US09194333B2
公开(公告)日：2015-11-24
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： F02K9/48 , F04D15/00 , F02K9/56
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。

26. 发明申请

US20150143797A1 TURBOPUMP 审中-公开
公开(公告)号：US20150143797A1
公开(公告)日：2015-05-28
申请号：US14408357
申请日：2013-06-14
申请人： SNECMA
发明人： Gaelle Le Bouar , Richard Petit
IPC分类号： F02K9/46
CPC分类号： F02K9/46 , F02K9/48 , F02K9/563 , F02K9/64 , F05D2270/051
摘要： A feed method for feeding reaction engines including off-loading a secondary flow of a first propellant downstream from a first pump but upstream from a first turbine that is driven by expansion of the first propellant and that drives at least the first pump. The off-loading is controlled in such a manner as to achieve equilibrium between power generated by the first turbine and power consumed by the first pump, thereby stopping a rise in speed of the first turbine and the first pump at a predetermined speed lower than a nominal speed.
摘要翻译：一种用于进料反应发动机的进料方法，包括将第一推进剂的二次流从第一泵的下游排出，但是通过第一推进剂的膨胀而被驱动并驱动至少第一泵的第一涡轮的上游。控制卸载的方式是实现第一涡轮机产生的动力与由第一泵消耗的功率之间的平衡，从而以比预定速度低的第一涡轮和第一泵的速度停止名义速度

27. 发明授权

US08528316B2 Solid propellant gas control system and method 失效
标题翻译：固体推进剂气体控制系统及方法
公开(公告)号：US08528316B2
公开(公告)日：2013-09-10
申请号：US12429003
申请日：2009-04-23
申请人： Mark H. Baker , Steve Abel , George Woessner
发明人： Mark H. Baker , Steve Abel , George Woessner
IPC分类号： F02K9/80 , F02K9/84 , F02K9/26 , F02K9/86
CPC分类号： F02K9/80 , F02K9/563 , F05D2270/051 , F05D2270/3013
摘要： Systems and methods of controlling solid propellant gas pressure and vehicle thrust are provided. Propellant gas pressure and a vehicle inertial characteristic are sensed. Propellant gas pressure commands and vehicle thrust commands are generated. A propellant gas pressure error is determined based on the propellant gas pressure commands and the sensed propellant gas pressure, and vehicle thrust error is determined based on the vehicle thrust commands and the sensed vehicle inertial characteristic. Reaction control valves are moved between closed and full-open positions based on the determined propellant gas pressure error and on the determined vehicle thrust error. The system and method allow the reaction control valves to operate at variable frequencies or at fixed frequencies. The system and method also allows propellant pressure to be commanded to follow a predetermined pressure profile or commanded to vary “on-the-fly.”
摘要翻译：提供了控制固体推进剂气体压力和车辆推力的系统和方法。检测到推进剂气体压力和车辆惯性特性。产生推进剂气体压力指令和车辆推力指令。基于推进剂气体压力指令和感测到的推进剂气体压力确定推进剂气体压力误差，并且基于车辆推力命令和所感测的车辆惯性特性来确定车辆推力误差。基于确定的推进剂气体压力误差和确定的车辆推力误差，反应控制阀在闭合位置和全开位置之间移动。该系统和方法允许反应控制阀以可变频率或固定频率运行。该系统和方法还允许命令推进剂压力遵循预定的压力分布或命令“即时”变化。

28. 发明授权

US08220267B1 Process to detect two-phase flow in a conduit 有权
标题翻译：在管道中检测两相流的过程
公开(公告)号：US08220267B1
公开(公告)日：2012-07-17
申请号：US12571579
申请日：2009-10-01
申请人： Elizabeth V Stein , Alex Pinera
发明人： Elizabeth V Stein , Alex Pinera
IPC分类号： F02C7/24
CPC分类号： F02K9/46 , F02C7/24 , F02K9/563 , F05D2260/80
摘要： A Helmholtz resonator is used to detect a presence of a two-phase flow in a conduit. The resonator is sized so that a range of frequencies it is tuned for corresponds to a change in the speed of sound as the fluid changes from all liquid, to liquid plus vapor, and to all vapor. A band-pass filter is used to cancel out any external noise that would pollute the signal from the resonator. The resonator is used to monitor for a two-phase flow occurring within a feed line leading into a turbopump of a rocket engine.
摘要翻译：亥姆霍兹共振器用于检测导管中两相流的存在。谐振器的尺寸使得其调谐的频率范围对应于随着流体从所有液体，液体加蒸汽和全部蒸汽变化而产生的声速变化。使用带通滤波器来抵消会污染来自谐振器的信号的任何外部噪声。谐振器用于监测在通向火箭发动机的涡轮泵的进料管线内发生的两相流。

29. 发明授权

US08005554B2 Device for controlling a regulated system, and an engine including such a device 有权
标题翻译：用于控制调节系统的装置和包括这种装置的发动机
公开(公告)号：US08005554B2
公开(公告)日：2011-08-23
申请号：US12389812
申请日：2009-02-20
申请人： Serge Le Gonidec
发明人： Serge Le Gonidec
IPC分类号： G06F19/00 , G05B19/18
CPC分类号： F02C9/26 , F02K9/563
摘要： This device for controlling at least one operating variable of a regulated system comprising: a filter module for filtering at least one setpoint input to the control device, the module using a first order integrator; and a correction module for correcting the variable by servo-control, the module taking account of a measurement of the variable and of the setpoint as filtered by the filter module in order to generate at least one command for the system; a control module suitable for generating a gain control factor α on the basis of at least one parameter of the system and of an operating limit value associated with the parameter; and weighting means for weighting the gain of the filter module as a function of the factor and of the residue between the setpoint and its filtered value.
摘要翻译：该装置用于控制调节系统的至少一个操作变量，包括：过滤器模块，用于过滤至少一个设定值输入到控制装置，该模块使用一阶积分器; 以及用于通过伺服控制来校正变量的校正模块，该模块考虑由过滤器模块过滤的变量和设定值的测量值，以便为系统生成至少一个命令; 控制模块，其适于基于所述系统的至少一个参数和与所述参数相关联的操作极限值来生成增益控制因子α; 以及加权装置，用于根据因子和设定点与其滤波值之间的残差来加权滤波器模块的增益。

30. 发明授权

US3581504A Monopropellant turbo gas generator 失效
标题翻译： MONOPROPELLANT涡轮发电机
公开(公告)号：US3581504A
公开(公告)日：1971-06-01
申请号：US3581504D
申请日：1968-08-28
申请人： AEROJET GENERAL CO
发明人： ANDRUS STANLEY R
IPC分类号： F02K9/48 , F02K9/56 , F02K9/68 , F02K9/02 , B01J9/04 , F04D15/00
CPC分类号： F02K9/48 , F02K9/563 , F02K9/68
摘要： A gas generator according to the present disclosure comprises a housing having an inlet opening for admitting monopropellant into the housing and an outlet having a back pressure control throat for expelling expanded gases therefrom. Impeller means is mounted within the housing for pressurizing the monopropellant. A turbine drive means is rotatably mounted within the housing adjacent the outlet for driving the impeller. Catalyst means is mounted within the housing intermediate the impeller and the turbine for decomposing the monopropellant. The gas generator operates in a pressure-amplifying staged expansion cycle in that the impeller means increases the pressure of the monopropellant before the monopropellant reaches the catalyst, and the monopropellant decomposes in the presence of the catalyst to produce exhaust gas of relatively high pressure. The gas is expanded in the first stage of expansion to drive the turbine means. The gas may be further expanded through the back pressure control throat to form a second stage of expansion. If desired, the outlet of the back pressure control throat may be contoured to form a divergent nozzle so the gas generator may be used as a turborocket engine.

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