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公开(公告)号：US20220268239A1
公开(公告)日：2022-08-25
申请号：US17740958
申请日：2022-05-10
摘要： A liquid rocket engine integrates tap-off openings at a combustion chamber wall to direct exhaust from the combustion chamber to a tap-off manifold that provides the exhaust to one or more auxiliary systems, such as a turbopump that pumps oxygen and/or fuel into the combustion chamber. The tap-off opening passes through a fuel channel formed in that combustion chamber exterior wall and receives fuel through a fuel opening that interfaces the fuel channel and tap-off opening. The tap-off manifold nests within a fuel manifold for thermal management. The fuel channel directs fuel into the combustion chamber through fuel port openings formed in the combustion chamber, the fuel port openings located closer to a headend of the combustion chamber than the tap-off openings.
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公开(公告)号：US11333104B1
公开(公告)日：2022-05-17
申请号：US16256206
申请日：2019-01-24
摘要： A liquid rocket engine cools a thruster body by pumping propellant through cooling channels integrated in the thruster body between internal and external surfaces. One or more of the cooling channel surfaces has a variable depth along a thrust axis to mix propellant flow and destroy thermal stratification, such as a depth that varies with a repeated contiguous sinusoidal form along the thrust axis. Fuel passed through the cooling channels injects from the combustion chamber wall towards a central portion of the combustion chamber to cross impinge with oxygen injected at the combustion chamber head so that a toroidal vortex forms to enhance propellant mixing.
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公开(公告)号：US11092111B1
公开(公告)日：2021-08-17
申请号：US16214588
申请日：2018-12-10
摘要： Embodiments of the present invention generally relate to a vapor retention device and methods of using a vapor retention device to manage propellant for upper stage space vehicles. The use of a vapor retention device, in combination with controlled acceleration, drives liquid propellant from a propellant supply line communicating with an upper stage main engine back into a propellant tank and establishes an insulating liquid/gas propellant interface that prevents the exchange of gaseous propellant across the interface.
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公开(公告)号：US10808967B2
公开(公告)日：2020-10-20
申请号：US15871361
申请日：2018-01-15
摘要： Closed-loop refrigeration cycles for liquid oxygen densification are disclosed. The disclosed refrigeration cycles may be turbine-based refrigeration cycles or a Joule-Thompson (JT) expansion valve based refrigeration cycles and include a refrigerant or working fluid comprising a mixture of neon or helium together with nitrogen and/or oxygen.
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公开(公告)号：US10557439B2
公开(公告)日：2020-02-11
申请号：US15771256
申请日：2016-10-20
摘要： An injection device, a combustor, and a rocket engine include a device main body partitioned into a fuel manifold and an oxidant manifold, and a plurality of injectors arranged at predetermined intervals in the device main body to inject fuel and oxidant into a combustion chamber, each of the injectors includes a LOx channel including a proximal end portion communicating with the oxidant manifold and a distal end portion communicating with the combustion chamber, a restrictor provided on the proximal end portion of the LOx channel and a GH2 channel including a proximal end portion communicating with the fuel manifold and a distal end portion communicating with the combustion chamber, and the restrictors have different shapes.
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公开(公告)号：US10408366B2
公开(公告)日：2019-09-10
申请号：US15039726
申请日：2014-11-17
申请人： SNECMA
摘要： A fastening method for fastening a tube (50) to a connector (101, 102), the method comprising the following steps: a) providing a connection kit comprising a sleeve, and a coupling for connecting together at least one pair of tubes, of generally tubular shape; b) placing the coupling in a first position in which the first end of the coupling projects outside the sleeve through a first end (10A) thereof; c) then fastening the first tube in leaktight manner to the first orifice; d) moving the coupling relative to the sleeve into a second position in which the first orifice lies inside the sleeve; and e) with the coupling in the second position, fastening the sleeve (10) at a sufficient distance from the coupling (20). A connection kit for performing the method.
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公开(公告)号：US10371098B2
公开(公告)日：2019-08-06
申请号：US14909945
申请日：2014-07-25
申请人： SNECMA
摘要： The device comprises a primary heater (58) suitable for heating the propellant coming from the tank (16) prior to it being reintroduced into its tank. The primary heater uses the heat of combustion from the engine (10) and the device further comprises a secondary heater (66) having its source of heat independent from the operation of the engine, the secondary heater being arranged downstream from the primary heater (58) in order to heat the propellant between its outlet from the primary heater and being reintroduced into the tank. The device also has means (62) between the feed to the primary heater (58) and the return of the propellant to the tank for putting the propellant under pressure.
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8.发明授权公开(公告)号：US10316794B2
公开(公告)日：2019-06-11
申请号：US14892001
申请日：2014-05-20
申请人： ECAPS AB
发明人： Göran Bergman , Kjell Anflo
摘要： The invention relates generally to dual mode bipropellant chemical rocket propulsion systems to be used in aerospace applications for 1) orbit raising, orbit maneuvers and maintenance, attitude control and deorbiting of spacecraft, and/or 2) propellant settling, attitude and roll control of missiles, launchers and space planes. The present invention also relates to a dual mode chemical rocket engine for use in such systems. The engine uses low-hazardous storable liquid propellants and can be operated either in monopropellant mode or in bipropellant mode. The monopropellants used are a low-hazard liquid fuel-rich monopropellant, and a low-hazard liquid oxidizer-rich monopropellant, respectively.
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公开(公告)号：US20190100475A1
公开(公告)日：2019-04-04
申请号：US15724086
申请日：2017-10-03
发明人： William M. Chew , Geoffrey H. Chew
摘要： Monopropellants comprising nonstoichiometric ratios of 2-hydroxyethylhydrazine cation (HEH+) and nitrate anion and water have improved thermal stability and fluid characteristics compared to nonstoichiometric ratios of HEH+ and nitrate anion without water. These monopropellants are useful for gas generators and rocket motors.
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公开(公告)号：US10247530B2
公开(公告)日：2019-04-02
申请号：US15217482
申请日：2016-07-22
申请人： Raytheon Company
摘要： A projectile, such as a railgun-launched projectile, includes a single-piece body that is additively manufactured. The single piece body includes fuel within it, and one or more cavities for receiving an oxidizer. The body also defines one or more combustion chambers therein for combustion of the fuel and oxidizer as part of a divert thruster system. Thus the projectile is able to fully contain the divert thruster system within the single-piece body without using any hot gas seals as part of the system. The body may also define a cavity for receiving a pressurized fluid, used as part of a cold-gas attitude control system of the projectile. The body may also define passages between the pressurized fluid cavity and other parts of the attitude control system, such as valves and/or nozzles that are outside of the body, for example being aft of the one-piece body.
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