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公开(公告)号：US20240318616A1
公开(公告)日：2024-09-26
申请号：US18731709
申请日：2024-06-03
申请人： Blue Origin, LLC
发明人： Mark David Horn , Adam Keith Norman
摘要： A variable flow area injector for a liquid rocket engine. The injector has a poppet with a variable outer width portion and a housing with a variable inner width portion. An annular flow path is defined between the variable width portions. Increased throttling of the engine passively increases the annular flow area of the injector by forcing the poppet in a distal direction. Decreased throttling allows a restoring spring to move the poppet in a proximal direction to decrease the annular flow area. A bellows can be included to dampen movement of the poppet. The bellows may be in a propellant-filled cavity separate from the main propellant flow path and have a series of openings through which the separate propellant flows.
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公开(公告)号：US12071915B2
公开(公告)日：2024-08-27
申请号：US18103460
申请日：2023-01-30
摘要： Various embodiments of a vortex hybrid motor are described herein. In some embodiments, the vortex hybrid motor may include a combustion zone defined by a fuel core and/or motor housing. The combustion zone may include an upper zone and a central zone that each contribute to thrust created by the vortex hybrid motor. In some embodiments, an injection port configuration is described that includes a proximal injection port that may be controlled for modulating a delivery of an amount of oxidizer for adjusting an oxidizer-to-fuel ratio. In some embodiments, a fuel core configuration is described that provides radially varying gradients of fuel in order to achieve desired thrust profiles. In some embodiments, the fuel core may include a support structure and/or a proximal end of a nozzle of the vortex hybrid motor may extend into the fuel core.
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公开(公告)号：US12012233B2
公开(公告)日：2024-06-18
申请号：US17740111
申请日：2022-05-09
CPC分类号： B64G1/402 , B64G1/64 , F02K9/42 , F02K9/44 , F02K9/46 , F02K9/50 , F02K9/56 , F02K9/566 , F02K9/58
摘要： Chemical propellant storage and supply systems and methods for use on spacecraft are provided. The systems and methods include a fluid pump for moving chemical propellant within the system at selected pressures. This can include operating the fluid pump to supply propellant to a thruster system at a selected pressure. A fuel tank can be refilled by connecting a propellant resupply source to the system, and operating the fluid pump to move propellant from the propellant resupply source to the fuel tank. In a system with multiple fuel tanks, the fluid pump can be operated to move propellant from a donor fuel tank to a recipient fuel tank. The chemical propellant can be stored in one or more fuel tanks at a relatively low pressure. In addition, the chemical propellant is not pressurized by a gaseous pressurant while it is stored in the fuel tank.
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公开(公告)号：US11982249B1
公开(公告)日：2024-05-14
申请号：US18133134
申请日：2023-04-11
发明人： Frank Charles Zegler
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.
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公开(公告)号：US11970995B2
公开(公告)日：2024-04-30
申请号：US17828868
申请日：2022-05-31
摘要： A rocket engine system having a heating system configured to heat an oxidizer; a combustion section having a flow path from an upstream inlet section through a restricted throat section to a downstream outlet section, the combustion section configured to accelerate the heated oxidizer as an oxidizer stream within the flow path in response to flow dynamics to supersonic speed; and a fuel system configured to introduce a fuel into the flow path to mix supersonically with the heated oxidizer to define a combined fuel and oxidizer stream at a first supersonic speed. The combined fuel and oxidizer stream undergoes a deflagration to denotation transition in the combustion section defined by an oblique shock wave and a normal shock wave that interact to achieve a standing detonation wave generally at an upstream portion of the restricted throat section configured such that combustion exits the downstream outlet section to provide thrust.
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公开(公告)号：US20240133352A1
公开(公告)日：2024-04-25
申请号：US18377983
申请日：2023-10-08
申请人： ATRX, Inc.
发明人： John A Bossard , John L Bergmans
IPC分类号： F02K7/16 , F01D9/04 , F02K3/10 , F02K3/12 , F02K7/18 , F02K9/08 , F02K9/26 , F02K9/30 , F02K9/42 , F02K9/48 , F02K9/76 , F02K9/78 , F02K9/97
CPC分类号： F02K7/16 , F01D9/041 , F02K3/10 , F02K3/12 , F02K7/18 , F02K9/08 , F02K9/26 , F02K9/30 , F02K9/42 , F02K9/48 , F02K9/76 , F02K9/78 , F02K9/97 , F05D2220/74 , F05D2240/128 , F05D2240/35
摘要： A Duplex Turbine Guide Vane (DTGV) assembly for a turbojet engine includes DTGVs arranged on a non-rotating guide vane ring configured to be positioned coaxially in apposition with a rotatable turbine wheel comprising turbine blades. Each of the DTGVs has an internal channel configured for receiving a gas and delivering the gas toward the turbine blades.
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公开(公告)号：US11933249B2
公开(公告)日：2024-03-19
申请号：US17811408
申请日：2022-07-08
申请人： Blue Origin, LLC
发明人： James R. French , Roger Eugene Ramsey , Adam Wuerl
摘要： Systems and methods for a fully reusable upper stage for a multi-stage launch vehicle are provided. The reusable upper stage uses an aerospike engine for main propulsion and for vertical landing. A heat shield can include a plurality of scarfed nozzles embedded radially around a semi-spherical surface of the heat shield, wherein inboard surfaces of the plurality of scarfed nozzles collectively define an aerospike contour. The heat shield can be actively cooled to dissipate heat encountered during reentry of the upper stage.
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公开(公告)号：US11897636B2
公开(公告)日：2024-02-13
申请号：US17505785
申请日：2021-10-20
申请人： ArianeGroup GmbH
发明人： Christian Hessel
IPC分类号： B64G1/40 , F02K9/42 , B64G1/42 , F17C7/02 , H01M8/0656
CPC分类号： B64G1/401 , B64G1/402 , B64G1/423 , F02K9/425 , F17C7/02 , H01M8/0656 , F17C2205/0332 , F17C2221/011 , F17C2221/012 , F17C2223/0161 , F17C2265/066 , F17C2270/0197 , H01M2250/20
摘要： A rocket propulsion system comprising a first cryogenic tank and a second cryogenic tank, wherein the first cryogenic tank is filled with a first propellant, and the second cryogenic tank is filled with a second propellant, for purposes of feeding at least one repeatedly ignitable main propulsion unit in a propulsion phase of the rocket propulsion system. For purposes of tank pressurization via at least a low level of acceleration in a ballistic phase, a first auxiliary propulsion unit can be operated by means of a first gas pressure accumulator, and at least one further auxiliary propulsion unit can be operated by means of a further gas pressure accumulator, and the rocket propulsion system is assigned an energy conversion unit, which is designed at least to charge the first and the second gas pressure accumulator, preferably in the ballistic phase.
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公开(公告)号：US20230332561A1
公开(公告)日：2023-10-19
申请号：US18026601
申请日：2021-09-13
发明人： Cheng CHENG , Haiqing ZHOU , Gui TIAN , Jingyu XIONG , Yeming ZENG , Guofeng ZHOU , Hongbo XU
摘要： A cryogenic engine for a space apparatus is provided. The cryogenic engine includes an injector body, a thrust chamber, and a spark plug, where the injector body is provided therein with an accommodating space; the spark plug is provided on one side of the injector body, and an electrode provided on the spark plug extends into the accommodating space; the thrust chamber is provided on the other side of the injector body and is communicated with the accommodating space; the injector body is provided with a combustion improver flow channel and a combustible agent flow channel; and the combustion improver flow channel and combustible agent flow channel are connected with the accommodating space.
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公开(公告)号：US20230323839A1
公开(公告)日：2023-10-12
申请号：US17704972
申请日：2022-03-25
申请人： MOMENTUS SPACE LLC
发明人： Joseph Oorebeek , Lee Wilson
摘要： A method for managing propellant in a spacecraft is disclosed. The method includes storing liquid propellant in a tank under an operating pressure controlled using a product of chemical decomposition of the propellant. The method may include transferring the liquid propellant out of the tank and chemically decomposing a portion of it using, for example electrolysis. Thus generated one or more gas components may be introduced to the tank to control the operating pressure in the tank.
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