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1. 发明授权

US12037963B1 Integrated vehicle fluids 有权
公开(公告)号：US12037963B1
公开(公告)日：2024-07-16
申请号：US18133111
申请日：2023-04-11
申请人： United Launch Alliance, L.L.C.
发明人： Frank Charles Zegler
IPC分类号： F02K9/58 , B64G1/40 , B64G1/42 , F02K9/42 , F02K9/44 , F02K9/50 , F02K9/60
CPC分类号： F02K9/58 , B64G1/402 , B64G1/421 , F02K9/42 , F02K9/44 , F02K9/50 , F02K9/60 , B64G1/401 , F02K9/425
摘要： A system and methods are disclosed for an upper stage space launch vehicle that uses gases from the propellant tanks to power an internal combustion engine that produces mechanical power for driving other components including a generator for generation of electrical current for operating compressors and fluid pumps and for charging batteries. These components and others comprise a thermodynamic system from which system enthalpy may be leveraged by extracting and moving heat to increase the efficient use of propellant and the longevity and performance of the launch vehicle.

2. 发明公开

US20240218844A1 ANNULAR VORTEX TANK VALVE FOR ROCKET MOTOR AND CONFIGURATION IN A ROCKET 审中-公开
公开(公告)号：US20240218844A1
公开(公告)日：2024-07-04
申请号：US18396488
申请日：2023-12-26
申请人： VAYA SPACE, INC.
发明人： Kineo WALLACE
IPC分类号： F02K9/44 , F02K9/42
CPC分类号： F02K9/44 , F02K9/425
摘要： A rocket engine is provided with a propellant valve controlling the output of a propellant tank. The valve is configured to induce a vortex in the propellant as it passes the propellant valve. Plural rocket engines may be supplied by a single valve, the valve inducing a vortex in the propellant which is then supplied to plural propellant lines configured to enhance the vortex induced by the valve.

3. 发明授权

US11852016B2 Rocket mining system, subsystems, components and methods 有权
公开(公告)号：US11852016B2
公开(公告)日：2023-12-26
申请号：US18044716
申请日：2021-08-17
申请人： Astrobotic Technology, Inc. , MASTEN SPACE SYSTEMS, INC.
发明人： Matthew Kuhns
IPC分类号： E21C51/00 , E21C37/16 , B01D8/00 , F02K9/42 , F02K9/80
CPC分类号： E21C51/00 , B01D8/00 , E21C37/16 , F02K9/425 , F02K9/80
摘要： Mining apparatuses, systems and methods related to the use of a rocket engine's plume and a collection manifold to efficiently displace, collect, process and store frozen volatiles embedded within or below a surface is disclosed. The plume contacts and churns up the surface. The frozen volatiles are displaced and/or evaporated within a closed environment under a collection manifold. The collection manifold has related components for addressing these frozen or gaseous volatiles downstream. Various apparatuses and subsystems are also disclosed including a rover, processing plants, collection manifold, and vapor manifold.

4. 发明公开

US20230323838A1 ADVANCED MONOPROPELLANT THRUSTER 审中-公开
公开(公告)号：US20230323838A1
公开(公告)日：2023-10-12
申请号：US18164369
申请日：2023-02-03
申请人： Skyrocket Industries, LLC
发明人： Jesse Dutton
IPC分类号： F02K9/42 , F02K9/68
CPC分类号： F02K9/425 , F02K9/68
摘要： A monopropellant rocket thruster includes a thruster, a pump, a decomposition catalyst, and an igniter. The thruster housing includes a reaction chamber and a divergent nozzle. The pump, coupled to the thruster housing, is operable to pump a monopropellant liquid into an inlet of the reaction chamber. The decomposition catalyst, located near the inlet between the pump and the reaction chamber, is configured to decompose at least one component of the monopropellant liquid into a mixture of liquid and gas in an exothermic reaction. The igniter is disposed at an outlet of the reaction chamber, such that the igniter ignites the mixture of liquid and gas for producing expanding gas into the divergent nozzle.

5. 发明公开

US20230202942A1 HOT-GAS-GENERATING APPARATUS WITH IONIC MONOPROPELLANT AND LOW VOLTAGE IGNITION 审中-公开
公开(公告)号：US20230202942A1
公开(公告)日：2023-06-29
申请号：US18175508
申请日：2023-02-27
申请人： Saverio NOBBE , LABORBITAL GMBH
发明人： Saverio NOBBE
IPC分类号： C06B33/12 , C06B25/34 , C06B23/00 , F02K9/42 , F23R3/28 , F02K9/52
CPC分类号： C06B33/12 , C06B23/002 , C06B23/007 , C06B25/34 , F02K9/52 , F02K9/425 , F23R3/28
摘要： A hot-gas-generating apparatus for reacting a propellant comprises a combustion chamber, at least one injector that is arranged upstream of the combustion chamber and can be closed, on the combustion chamber side, to the propellant, electrodes being integrated in said injector, and at least one supply line for the propellant. In this context, the propellant is a monopropellant and a substantially water-free ionic solution having low vapor pressure, preferably with a residual water content of less than five percent by mass, which is capable of self-sustaining combustion at a given combustion chamber pressure, and the electrodes have at least two electrodes of opposite polarity which are suitable for electrically igniting the propellant by means of a flow of current through the propellant when this propellant flows between the opposite-polarity electrodes.

6. 发明申请

US20170254296A1 Rocket Engine Bipropellant Supply System 审中-公开
公开(公告)号：US20170254296A1
公开(公告)日：2017-09-07
申请号：US15059884
申请日：2016-03-03
申请人： Daniel Patrick Weldon , Kevin Patrick Weldon
发明人： Daniel Patrick Weldon , Kevin Patrick Weldon
IPC分类号： F02K99/00 , F02K9/42 , F02K9/60 , F02K9/97
CPC分类号： F02K9/605 , F02K9/425 , F02K9/44 , F02K9/972
摘要： According to one contemplated embodiment of the rocket engine invention, water is first pumped from a water tank through a rocket nozzle cooling heat exchanger wherein it is evaporated into said superheated steam. A generator supplies electricity to an electrolyzer that electrolyzes superheated steam into gaseous hydrogen and gaseous oxygen. The gaseous hydrogen and gaseous oxygen is employed for forming an annular curtain of secondary combustion in a divergent rocket engine. The secondary combustion gas surrounds a central thrust of combustion gas produced in an upstream combustion chamber by a primary injection of hydrogen/oxygen supplied from a liquid hydrogen tank and liquid oxygen tank. The rocket liquid hydrogen tank and liquid oxygen tank are pressurized by gaseous hydrogen and gaseous oxygen generated by the electrolyzer.

7. 发明申请

US20160281641A1 A PROPULSION ASSEMBLY AND A METHOD OF FEEDING PROPELLANTS 审中-公开
标题翻译：一种推进装置和一种饲料推进剂的方法
公开(公告)号：US20160281641A1
公开(公告)日：2016-09-29
申请号：US15034215
申请日：2014-11-05
申请人： SNECMA
发明人： François DANGUY , David HAYOUN , Jean Michel SANNINO
IPC分类号： F02K9/42 , F02K9/48
CPC分类号： F02K9/425 , F02K9/48 , F02K9/50 , F02K9/64 , F02K9/972
摘要： The invention relates to the field of rocket engines, and more particularly to a propulsion assembly (10) comprising a first tank (11) for a first liquid propellant, a second tank (12) for a second liquid propellant, a pressurizer device (60) configured to maintain a substantially higher pressure in the second tank (12) than in the first tank (11), and a single-shaft turbopump (30) comprising a turbine (33), a first pump (31), and a second pump (32). The turbine (33) is actuated by expansion of the first propellant after it has passed through a regenerative heat exchanger (44), and in turn it acts via the single rotary shaft (34) of the turbopump (30) to drive said first and second pumps (31, 32) respectively pumping said first and second propellants in order to feed a propulsion chamber (40).
摘要翻译：本发明涉及火箭发动机领域，更具体地涉及一种推进组件（10），其包括用于第一液体推进剂的第一罐（11），用于第二液体推进剂的第二罐（12），加压装置（60））构造成在第二箱（12）中保持比在第一箱（11）中显着更高的压力，以及单轴涡轮泵（30），其包括涡轮机（33），第一泵（31）和第二泵泵（32）。第一推进剂在其通过再生热交换器（44）之后的膨胀致动涡轮（33），并且再次通过涡轮泵（30）的单个旋转轴（34）作用以驱动所述第一推进剂和分别泵送所述第一和第二推进剂以便馈送推进室（40）的第二泵（31,32）。

8. 发明申请

US20150027102A1 TRI-PROPELLANT ROCKET ENGINE FOR SPACE LAUNCH APPLICATIONS 审中-公开
标题翻译： TRI-PROPELLANT发动机用于空间启动应用
公开(公告)号：US20150027102A1
公开(公告)日：2015-01-29
申请号：US14217469
申请日：2014-03-17
申请人： PATRICK R.E. BAHN , EARL W. RENAUD
发明人： PATRICK R.E. BAHN , EARL W. RENAUD
IPC分类号： F02K9/42
CPC分类号： F02K9/425 , F02K9/46
摘要： A tri-propellant rocket engine for space launch applications is disclosed. The tri-propellant rocket engine comprises three main assemblies: an injector, a chamber head, and a chamber.
摘要翻译：公开了一种用于太空发射应用的三推进剂火箭发动机。三推进剂火箭发动机包括三个主要组件：喷射器，腔室头部和腔室。

9. 发明申请

US20140260179A1 System, Method and Apparatus for Lean Combustion with Plasma from an Electrical Arc 有权
标题翻译：用于从电弧等离子体的精细燃烧的系统，方法和装置
公开(公告)号：US20140260179A1
公开(公告)日：2014-09-18
申请号：US14288898
申请日：2014-05-28
申请人： FORET PLASMA LABS, LLC
发明人： Todd Foret
IPC分类号： F02K9/42
CPC分类号： F02K3/12 , B64G1/405 , B64G1/406 , F01D13/00 , F02C3/14 , F02C7/266 , F02K9/425 , F23R3/007 , F23R3/58 , F23R2900/00002 , F23R2900/00009 , G21D5/02 , H05H1/24 , H05H1/32 , H05H1/48 , H05H2001/4695 , Y02E50/12 , Y02T50/678
摘要： The present invention provides a plasma arc torch that can be used for lean combustion. The plasma arc torch includes a cylindrical vessel, an electrode housing connected to the first end of the cylindrical vessel such that a first electrode is (a) aligned with a longitudinal axis of the cylindrical vessel, and (b) extends into the cylindrical vessel, a linear actuator connected to the first electrode to adjust a position of the first electrode, a hollow electrode nozzle connected to the second end of the cylindrical vessel such that the center line of the hollow electrode nozzle is aligned with the longitudinal axis of the cylindrical vessel, and wherein the tangential inlet and the tangential outlet create a vortex within the cylindrical vessel, and the first electrode and the hollow electrode nozzle create a plasma that discharges through the hollow electrode nozzle.
摘要翻译：本发明提供了可用于稀薄燃烧的等离子弧焊炬。等离子弧焊炬包括圆柱形容器，连接到圆柱形容器的第一端的电极壳体，使得第一电极（a）与圆柱形容器的纵向轴线对准，并且（b）延伸到圆柱形容器中，连接到第一电极以调节第一电极的位置的线性致动器，连接到圆柱形容器的第二端的中空电极喷嘴，使得中空电极喷嘴的中心线与圆柱形容器的纵向轴线对准并且其中所述切向入口和所述切向出口在所述圆柱形容器内产生涡流，并且所述第一电极和所述中空电极喷嘴产生通过所述中空电极喷嘴排出的等离子体。

10. 发明申请

US20120269633A1 CLOSED GAS GENERATOR AND MICRO POWER UNIT INCLUDING THE SAME 有权
标题翻译：封闭式气体发生器和微功率单元，包括它们
公开(公告)号：US20120269633A1
公开(公告)日：2012-10-25
申请号：US13089441
申请日：2011-04-19
申请人： Jeremy C. Danforth , Richard D. Loehr , Kevin P. Murphy
发明人： Jeremy C. Danforth , Richard D. Loehr , Kevin P. Murphy
IPC分类号： B64D27/24 , H02K7/18 , H02J7/00 , F02K9/62 , F02K1/00
CPC分类号： F02K9/00 , B64C2201/042 , F02K9/42 , F02K9/425 , F02K9/50 , F02K9/52 , F02K9/68 , H02J7/00 , H02K7/1823
摘要： A gas generator assembly includes a propellant chamber housing an amine based propellant. A reaction chamber is coupled with the propellant chamber. The reaction chamber includes a reaction chamber housing, and a porous reaction matrix within the reaction chamber housing. The reaction matrix includes a catalyzing agent, and the catalyzing agent is configured to non-combustibly catalyze the amine based propellant into one or more pressurized gases. An injector is in communication with the propellant chamber. The injector is configured to deliver the amine based propellant to the porous reaction matrix. A discharge nozzle is coupled with the reaction chamber and is configured to accelerate and discharge the one or more pressurized gases. In one example, the gas generator is coupled with one or more of an impulse turbine assembly and an electric generator to form a micro power unit.
摘要翻译：气体发生器组件包括容纳胺基推进剂的推进剂室。反应室与推进剂室结合。反应室包括反应室壳体和反应室壳体内的多孔反应基质。反应基质包括催化剂，并且催化剂被配置为不可燃地将胺基推进剂催化成一种或多种加压气体。喷射器与推进剂室连通。喷射器构造成将胺基推进剂输送到多孔反应基质。排放喷嘴与反应室联接并且构造成加速和排出一个或多个加压气体。在一个示例中，气体发生器与脉冲涡轮机组件和发电机中的一个或多个耦合以形成微动力单元。

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