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1. 发明授权

US11498705B1 On orbit fluid propellant dispensing systems and methods 有权
公开(公告)号：US11498705B1
公开(公告)日：2022-11-15
申请号：US16871144
申请日：2020-05-11
申请人： Ball Aerospace & Technologies Corp.
发明人： Gordon C. Wu , Derek Chan , Suzan Q. Green
IPC分类号： B64G1/40 , F02K9/50 , F02K9/58 , F02K9/44 , B64G5/00 , F02K9/60
摘要： Systems and methods for refueling a chemical propulsion system are provided. The systems can include multiple pressurant reservoirs to supply pressure to one or more fuel tanks. During a refueling operation, pressurant is released, fuel is added to the fuel tank, and then the fuel tank is repressurized using pressurant from a secondary pressurant tank. In other configurations, during a refueling operation pressurant is cooled to depressurize the fuel tank, fuel is added to the fuel tank, and then the pressurant is heated to repressurize the fuel tank. The systems and methods can be used to refuel operationally deployed space craft.

2. 发明申请

US20220290635A1 HYBRID SOLAR THERMAL AND CHEMICAL VEHICLE CONFIGURATIONS FOR SPACE MINING APPLICATIONS 有权
公开(公告)号：US20220290635A1
公开(公告)日：2022-09-15
申请号：US17827429
申请日：2022-05-27
申请人： Trans Astronautica Corporation
发明人： Joel C. Sercel , Philip J. Wahl , James G. Small
IPC分类号： F02K9/50 , E21C51/00 , F02K9/68 , F02K9/64
摘要： Solar thermal and chemical hybrid rocket configurations for mining and other space applications are disclosed. One aspect is a rocket propulsion system configured to provide rocket thrust, including a solar absorber, a rocket nozzle, and a solar power collection system configured to collect solar energy from the sun, generate an energy beam from the collected sunlight, heat the solar absorber to transfer heat to one or more pressurized propulsive gases, and expel the heated pressurized propulsive gases through a rocket nozzle. A solar absorber can be formed from a granular collection or agglomeration of solids (e.g., of beads), which can be layered with more transparent layer(s) above and more absorbing layer(s) below to create a temperature profile in propellant(s) flowing through the absorber. A hybrid motor can provide an energy (e.g., solar) absorber for absorbing and transferring radiative energy as well as a combustion area. Multiple propellants can be present in a single chamber and be forced from a nozzle to produce thrust. Pressure in a rocket can be achieved from heating inert gasses, and alternatively or simultaneously, from mixing and igniting non-inert gasses.

3. 发明授权

US11371468B2 Supply system for supplying a rocket engine 有权
公开(公告)号：US11371468B2
公开(公告)日：2022-06-28
申请号：US16636234
申请日：2018-08-21
申请人： ARIANEGROUP SAS
发明人： Benoît Mathieu André Cingal , Philippe Becret , Mathieu Henry Raymond Triger
IPC分类号： F02K9/56 , F02K9/50 , F02K9/60 , F16L55/052 , F02K9/44
摘要： A supply system for supplying a rocket engine with at least one propellant, the supply system comprising at least one supply circuit able to circulate the propellant, and at least one reservoir in fluid communication with the supply circuit via at least one communication pipe, so that a fluid contained in the reservoir can flow from the latter up to the supply circuit, and vice versa, via said at least one communication pipe, the reservoir being able to contain a volume of gas, and heating means able to vary the volume of gas in the reservoir, the heating means being configured to vaporize the propellant in the reservoir.

4. 发明授权

US11156516B2 Abnormality determination device and abnormality determination method 有权
公开(公告)号：US11156516B2
公开(公告)日：2021-10-26
申请号：US16085791
申请日：2016-12-19
申请人： IHI Corporation
发明人： Hatsuo Mori , Keisuke Suzuki , Noriyoshi Mizukoshi , Takashi Ogai
IPC分类号： G01L7/18 , F02K9/52 , F04D29/22 , F04D15/00 , G01M13/00 , G01M5/00 , G05B23/02 , F02K9/46 , F02K9/50 , G01L27/02
摘要： An abnormality determination device according to one aspect of the present disclosure is an abnormality determination device that determines an abnormality of an inducer used for a pump, the abnormality determination device including a stress-response acquisition unit that acquires a stress response indicating a temporal change in stress applied to the inducer, an accumulated-fatigue-damage-degree calculation unit that calculates an accumulated fatigue-damage degree of the inducer based on the stress response, a lifetime-consumption-rate calculation unit that calculates a lifetime consumption rate that is a changing rate of the accumulated fatigue-damage degree with respect to time, and a determination unit that determines an abnormality of the inducer based on the accumulated fatigue-damage degree and the lifetime consumption rate, in which the inducer is used only for a predetermined use time per operation of the pump.

5. 发明授权

US10989144B2 Injection element having an ignition device 有权
公开(公告)号：US10989144B2
公开(公告)日：2021-04-27
申请号：US16073180
申请日：2017-01-26
申请人： ARIANEGROUP SAS
发明人： Jean-Luc Le Cras , Laurent Gomet
IPC分类号： F02K9/52 , F02K9/95 , F02K9/44 , F02K9/46 , F02K9/48 , F02K9/42 , F02K9/50 , B64G1/40
摘要： An injector element for injecting a mixture of at least a first propellant and a second propellant into a combustion chamber. The injector element includes a first tubular wall defining a first duct for injecting the first propellant, and a second wall surrounding the first wall and defining, between the first and second walls, a second duct for injecting the second propellant. The first wall includes a first electrode for igniting the mixture by electric discharge.

6. 发明申请

US20200025386A1 LEAN BURN FUEL INJECTOR 审中-公开
公开(公告)号：US20200025386A1
公开(公告)日：2020-01-23
申请号：US16276669
申请日：2019-02-15
申请人： ROLLS-ROYCE plc
发明人： Carl L. MULDAL , Luca TENTORIO , Hua Wei HUANG , Juan Carlos ROMAN CASADO
IPC分类号： F23R3/34 , F02K9/50 , F23R3/14
摘要： A lean burn fuel injector has a head which has a coaxial arrangement of an inner pilot air-blast fuel injector and an outer main air-blast fuel injector. The pilot fuel injector comprises coaxially arranged inner and outer air swirler passages. The main fuel injector comprises coaxially arranged inner and outer air swirler passages. A first splitter is arranged between the passages. The first splitter has a conical divergent downstream portion. A second splitter is arranged radially within and spaced from the first splitter. The second splitter has a conical convergent portion and a conical divergent downstream portion. The downstream end of the second splitter is upstream of the downstream end of the first splitter. A connecting member connects the downstream end of the second splitter and the downstream portion of the first splitter upstream of the downstream end of the first splitter to form a sharp edge.

7. 发明授权

US10533523B2 Device for pressurizing propellant tanks of a rocket engine 有权
公开(公告)号：US10533523B2
公开(公告)日：2020-01-14
申请号：US14909894
申请日：2014-07-25
申请人： SNECMA
发明人： Gérard Roz , Lauren Nguyen Duc , Stéphanie Dreyer , Nicolas Ravier
IPC分类号： F02K9/50 , F02K9/94 , F02K9/97
摘要： The device comprises two heat exchangers (74, 90) suitable respectively for vaporizing first and second propellants before they are reintroduced in gaseous form into their tanks (16, 18). The heat exchangers co-operate respectively with first and second gas generators (60, 84) suitable for being fed with a mixture of propellants in order to produce combustion, the second gas generator (84) being suitable for being fed at least in part by the exhaust from the first gas generator (60).

8. 发明申请

US20190011085A1 DETERMINING A GAS VOLUME IN A TANK DEVICE 审中-公开
公开(公告)号：US20190011085A1
公开(公告)日：2019-01-10
申请号：US16026255
申请日：2018-07-03
申请人： ArianeGroup GmbH
发明人： Johannes Sebald
IPC分类号： F17C13/02 , F17C13/04 , F17C13/00 , G01F22/02 , F02K9/50 , F02K9/56
摘要： A tank device for a tank liquid comprises a pressure vessel with a first chamber for the tank liquid and second chamber arranged in an interior of the tank. The first and second chamber are closed off with respect to each other and are in operative connection via at least one membrane which separates the first and second chambers and is capable of vibration. The tank device further comprises a controllable element for effecting a pressure surge in the pressure vessel, a pressure sensor for detecting a pressure vibration resulting from the pressure surge and a temperature sensor for measuring a temperature prevailing in the pressure vessel. An evaluation device of the tank device is configured to determine a current gas volume in the pressure vessel from a respectively detected pressure vibration and a measured temperature to thereby calculate the mass of the tank liquid.

9. 发明授权

US10072610B2 Method and a device for feeding a rocket engine 有权
公开(公告)号：US10072610B2
公开(公告)日：2018-09-11
申请号：US14440835
申请日：2013-11-04
申请人： SNECMA
发明人： Jean Michel Sannino , François Lassoudiere , David Hayoun
IPC分类号： F02K9/48 , F02K9/50 , F02K9/97 , F02K9/64
CPC分类号： F02K9/48 , F02K9/50 , F02K9/64 , F02K9/972
摘要： The invention relates to a feed device for feeding a thrust chamber (10) of a rocket engine (100) with first and second propellants. According to the invention, a first feed circuit (16) of the thrust chamber (10) comprises a turbopump (22) having at least one pump (22a) for pumping the first propellant from a first tank (12), and a turbine (22b) mechanically coupled to said pump (22a). The first feed circuit connects an outlet of the pump to an inlet of the turbine via a heat exchanger (24) configured to heat the first propellant with heat generated by the thrust chamber, in order to actuate the turbine. According to the invention, a second feed circuit (18) is configured to feed the thrust chamber with second propellant from a second tank (14) that is configured to be pressurized. The invention also provides a method of feeding a rocket engine thrust chamber with first and second propellants.

10. 发明申请

US20160160801A1 PREMIXED LIQUID PROPELLANT PROPULSION SYSTEM AND METHOD WITH ANTI-FLASHBACK QUENCHING LIQUID INJECTOR 有权
标题翻译：具有防反射液体注射器的优先液体推进式推进系统和方法
公开(公告)号：US20160160801A1
公开(公告)日：2016-06-09
申请号：US14229823
申请日：2014-03-28
申请人： The Boeing Company
发明人： Anthony D. Straw , Mark J. Holthaus , Steven J. Hoeser
IPC分类号： F02K9/50 , F02K9/42
CPC分类号： F02K9/50 , F02K9/42 , F02K9/52
摘要： A liquid injector system for a combustion engine, having a single feed inlet configured to receive a premixed liquid propellant under pressure or a purge gas under pressure, and having a liquid injector assembly. The assembly has a liquid injector having a hollow dome and injector holes configured to receive and inject the premixed liquid propellant or the purge gas through the liquid injector and into a combustion chamber. The liquid injector system has a liquid-to-gas zone between an injector outlet side and a flame front. A pressure gradient decrease between the liquid injector and the combustion chamber causes the premixed liquid propellant to expand from liquid to gas phases, which causes a temperature decrease at the liquid-to-gas zone, wherein the pressure gradient decrease and the temperature decrease prevent or mitigate the flame front from propagating upstream of the combustion chamber, which achieves an anti-flashback quenching liquid injector design.
摘要翻译：一种用于燃烧发动机的液体喷射器系统，具有单个进料入口，其构造成在压力下接收预混合液体推进剂或在压力下接收吹扫气体，并具有液体喷射器组件。组件具有液体注射器，其具有中空圆顶和喷射器孔，其构造成接收并注入预混合液体推进剂或吹扫气体通过液体喷射器并进入燃烧室。液体注射器系统在喷射器出口侧和火焰前端之间具有液体 - 气体区域。液体喷射器和燃烧室之间的压力梯度减小导致预混合液体推进剂从液体膨胀到气相，这导致液体 - 气体区域的温度降低，其中压力梯度降低和温度降低阻止或减轻火焰前沿从燃烧室的上游传播，实现了防回闪淬火液体喷射器的设计。

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