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公开(公告)号：US12065991B2
公开(公告)日：2024-08-20
申请号：US17514471
申请日：2021-10-29
申请人： Blue Origin, LLC
CPC分类号： F02K9/974 , B32B5/024 , B32B5/26 , B32B7/027 , B32B7/09 , B32B7/12 , B64G1/226 , B64G1/58 , F02K9/97 , F02K9/972 , B32B2262/103 , B32B2262/105 , B32B2307/304 , B32B2605/00 , B32B2605/18
摘要： A high temperature thermal protection systems for rockets, and associated methods, is disclosed. A representative system includes a launch vehicle having a first end and a second end generally opposite the first end. The launch vehicle is elongated along a vehicle axis extending between the first and second ends and carries a propulsion system having at least one nozzle positioned at the second end of the launch vehicle. A thermal protection apparatus positioned around the nozzle is used to provide cooling and/or insulation to the nozzle during the flight of the launch vehicle. The thermal protection apparatus can include multiple fabric layers and an insulation layer stacked and stitched together. The fabric layers can include metal alloy fibers. In representative systems, the thermal protection apparatus can further include provisions for water that saturates the insulation layer to provide further insulating and/or cooling effects.
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公开(公告)号：US20240271589A1
公开(公告)日：2024-08-15
申请号：US18689354
申请日：2022-08-31
申请人： Pramod VADTYA , Anil Kumar Kommagalla VELDI , Abhijeet INAMDAR , Lars-Erik ROBERTSEN , SirinoR AS
CPC分类号： F02K7/00 , F02K9/97 , F05D2220/70
摘要： Supersonic jet engine includes a housing and an exhaust nozzle. Spike extends outwardly from the housing. Plurality of fans are arranged in an axial direction within the housing, each of the plurality of fans includes a plurality of fan blades. Plurality of turbines are included, and each of the plurality of turbines having a plurality of turbine blades and being arranged and coupled to a respective one of the fans in a radial direction. Plurality of radial compressors are located radially from the each of the plurality of turbines and are operable to drivingly rotate the respective turbine, which in turn rotates the respective fan. Plurality of electric motors are included, and each of the plurality of electric motors are coupled to a respective one of the plurality of radial compressors and drivingly rotating the respective radial compressor.
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公开(公告)号：US12031507B2
公开(公告)日：2024-07-09
申请号：US17754787
申请日：2020-08-27
发明人： Andrew Lapsa , Thomas Feldman
CPC分类号： F02K9/97 , B64G1/006 , F02K9/64 , F02K9/972 , F05D2240/1281
摘要： An augmented aerospike nozzle includes a throat, a centerbody extending aft of the throat, an inner expansion surface defined by the centerbody, an outer expansion surface outboard of the inner expansion surface, and an expansion cavity defined between the inner expansion surface and the outer expansion surface. An engine includes a high pressure chamber and the augmented aerospike nozzle. A vehicle for supersonic flight includes the engine with the augmented aerospike nozzle.
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公开(公告)号：US11976613B1
公开(公告)日：2024-05-07
申请号：US18457283
申请日：2023-08-28
申请人： Pivotal Space, Inc.
发明人： Lloyd J. Droppers
摘要： A rocket propulsion system that may include a supersonic rocket nozzle with a supersonic divergent section, and a heat transfer system configured to transfer heat from the supersonic rocket nozzle to a propellant where a portion of the propellant may be selectively injected, combusted, and expanded in the supersonic nozzle generating an additional thrust. In examples, the heated propellant may be used to power a pump system to feed the rocket engine.
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公开(公告)号：US20230358516A1
公开(公告)日：2023-11-09
申请号：US17662620
申请日：2022-05-09
申请人： James Michael Holst
发明人： James Michael Holst
摘要： To use launchpad based laser beam generators to stream 50+ kilowatt laser beams up through clear fused quartz discs located in the base of the rocket to super heat the steam in the rocket's pressure chamber for the purpose of increasing the thrusting power of the rocket. This rocket does not use fossil fuel, but rather it uses 99% pure hydrogen peroxide fuel, (H2O2) which flashes into steam without the use of combustion.
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6.发明公开公开(公告)号：US20230184199A1
公开(公告)日：2023-06-15
申请号：US17999343
申请日：2021-05-11
申请人： ARIANEGROUP SAS
发明人： Alban DU TERTRE , Didier GUICHARD
摘要： Piece comprising a first metal part and a second part in organic matrix composite material, wherein the first part has a first connecting portion and the second part has a second connecting portion, the second connecting portion having at least one through-hole, the second connecting portion being totally or partially sandwiched between the first connecting portion and a metal fastening element, the fastening element being fastened on the first part both onto the first connecting portion via the through-hole of the second connecting portion and onto a portion other than the first connecting portion, whereby the first part and the second part are fastened to each other.
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7.发明公开公开(公告)号：US20230184198A1
公开(公告)日：2023-06-15
申请号：US17999319
申请日：2021-05-11
申请人： ARIANEGROUP SAS
摘要： The invention relates to a piece comprising a first metal part and a second part made of an organic matrix composite material, in which the first part has a first connecting portion and the second part has a second connecting portion, the second connecting portion having at least one blind hole, the second connecting portion being totally or partially sandwiched between the first connecting portion and a metal fastening element, the fastening element being fastened to the first part on a portion other than the first connecting portion and extending into the at least one blind hole, whereby the first part and the second part are fastened to one another.
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公开(公告)号：US11661910B2
公开(公告)日：2023-05-30
申请号：US17048243
申请日：2019-04-18
申请人： CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE , UNIVERSITE D'ORLEANS , UNIVERSITE D'EVRY-VAL D'ESSONNE
发明人： Luc Leger , Vladeta Zmijanovic , Mohamed Sellam , Amer Chpoun
CPC分类号： F02K9/97 , F02K1/28 , F02K1/30 , F02K9/82 , F05D2220/323 , F05D2240/128 , F05D2250/324 , F05D2250/713
摘要： A mixing tube with multiple shapes is provided, allowing additional injection of gas in order to keep the flow detached from the second shape in an ascent phase and to bring about, in a descent phase, a controlled detachment as a result of the change of slope between the two shapes. A propulsion nozzle for an engine of a spacecraft or aircraft is provided including such a mixing tube and a method for controlling the speed transition of the propulsion gases in such a nozzle in accordance with the altitude. Also, a method is provided for vectorising the thrust in such a nozzle by radial and asymmetrical injection of gas and a control method which prevents re-attachment of the jet to the second shape of such a propulsion nozzle for an engine of a spacecraft when it is in the take-off or landing phase.
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公开(公告)号：US11643367B2
公开(公告)日：2023-05-09
申请号：US16595488
申请日：2019-10-08
发明人： Mau-Yi Huang , Hao-Chung Hsiao
IPC分类号： C04B35/83 , C04B35/634 , C04B35/628 , F02K9/97
CPC分类号： C04B35/83 , C04B35/62873 , C04B35/62884 , C04B35/62886 , C04B35/62894 , C04B35/634 , C04B2235/422 , C04B2235/5232 , C04B2235/5248 , C04B2235/5256 , F02K9/97
摘要： A composite material fabrication method includes stacking a plurality of fiber layers and a first binder and curing the first binder to form a three-dimensional structure with a plurality of mesh openings, and filling the plurality of mesh openings with a plurality of fiber filaments of a fiber array and a second binder and curing the second binder. A plurality of first mesh openings of the plurality of mesh openings are connected in a first direction.
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公开(公告)号：US11629669B1
公开(公告)日：2023-04-18
申请号：US16831025
申请日：2020-03-26
申请人： EXQUADRUM, INC.
发明人： Kevin E. Mahaffy , Marlow Moser
摘要： A solid rocket motor is described that includes a solid propellant section, a nozzle, and a source of monopropellant, such as liquid monopropellant. The monopropellant is used to control various operational parameters of the solid rocket motor, such as thrust vector control, roll control, extinguishment of the motor, and cooling of the nozzle and/or nozzle throat. The nozzle and the nozzle throat can be an integrated, single piece assembly that facilitates re-use of the nozzle.
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