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公开(公告)号：US20240278938A1
公开(公告)日：2024-08-22
申请号：US18632124
申请日：2024-04-10
Applicant: Blue Origin, LLC
Inventor： Zachary Reid Tolley
CPC classification number: B64G1/408 , F02K9/42 , F02K9/425 , F02K9/44 , F02K9/50 , F02K9/64 , G21D5/02 , F02K9/46
Abstract: Systems and methods for nuclear reactor direct drive of a cryocooler turbine. A nuclear thermal propulsion (NTP) system may have a nuclear reactor that heats a thermal working fluid for directly driving the turbine to power a cryogenic fluid management (CFM) system for keeping propellant at cryogenic temperatures. The features may be used on NTP rockets. The propellant may be liquid hydrogen.
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公开(公告)号：US11498705B1
公开(公告)日：2022-11-15
申请号：US16871144
申请日：2020-05-11
Applicant: Ball Aerospace & Technologies Corp.
Inventor： Gordon C. Wu , Derek Chan , Suzan Q. Green
Abstract: 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.
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公开(公告)号：US20220290635A1
公开(公告)日：2022-09-15
申请号：US17827429
申请日：2022-05-27
Applicant: Trans Astronautica Corporation
Inventor： Joel C. Sercel , Philip J. Wahl , James G. Small
Abstract: 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.
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公开(公告)号：US11371468B2
公开(公告)日：2022-06-28
申请号：US16636234
申请日：2018-08-21
Applicant: ARIANEGROUP SAS
IPC: F02K9/56 , F02K9/50 , F02K9/60 , F16L55/052 , F02K9/44
Abstract: 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.
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公开(公告)号：US11156516B2
公开(公告)日：2021-10-26
申请号：US16085791
申请日：2016-12-19
Applicant: IHI Corporation
Inventor： Hatsuo Mori , Keisuke Suzuki , Noriyoshi Mizukoshi , Takashi Ogai
IPC: G01L7/18 , F02K9/52 , F04D29/22 , F04D15/00 , G01M13/00 , G01M5/00 , G05B23/02 , F02K9/46 , F02K9/50 , G01L27/02
Abstract: 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.
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Patent Agency Ranking
公开(公告)号：US10989144B2
公开(公告)日：2021-04-27
申请号：US16073180
申请日：2017-01-26
Applicant: ARIANEGROUP SAS
Inventor： Jean-Luc Le Cras , Laurent Gomet
Abstract: 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.
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公开(公告)号：US20200025386A1
公开(公告)日：2020-01-23
申请号：US16276669
申请日：2019-02-15
Applicant: ROLLS-ROYCE plc
Inventor： Carl L. MULDAL , Luca TENTORIO , Hua Wei HUANG , Juan Carlos ROMAN CASADO
Abstract: 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.
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公开(公告)号：US10533523B2
公开(公告)日：2020-01-14
申请号：US14909894
申请日：2014-07-25
Applicant: SNECMA
Inventor： Gérard Roz , Lauren Nguyen Duc , Stéphanie Dreyer , Nicolas Ravier
Abstract: 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).
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公开(公告)号：US20190011085A1
公开(公告)日：2019-01-10
申请号：US16026255
申请日：2018-07-03
Applicant: ArianeGroup GmbH
Inventor： Johannes Sebald
Abstract: 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.
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公开(公告)号：US10072610B2
公开(公告)日：2018-09-11
申请号：US14440835
申请日：2013-11-04
Applicant: SNECMA
Inventor： Jean Michel Sannino , François Lassoudiere , David Hayoun
Abstract: 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.
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