公开(公告)号：US12025076B1

公开(公告)日：2024-07-02

申请号：US18396488

申请日：2023-12-26

Applicant: VAYA SPACE, INC.

Inventor： Kineo Wallace

IPC: F02K9/58 ,  B64G5/00 ,  F02K9/42 ,  F02K9/44 ,  F02K9/76

CPC classification number: F02K9/44 ,  B64G5/00 ,  F02K9/425 ,  F02K9/58 ,  F02K9/76 ,  Y10T137/87088 ,  Y10T137/87153 ,  Y10T137/87764

Abstract: A rocket engine is provided with a propellant valve controlling the output of a propellant tank. The valve is configured to induce a vortex in the propellant as it passes the propellant valve. Plural rocket engines may be supplied by a single valve, the valve inducing a vortex in the propellant which is then supplied to plural propellant lines configured to enhance the vortex induced by the valve.

公开(公告)号：US11680544B1

公开(公告)日：2023-06-20

申请号：US17404666

申请日：2021-08-17

Applicant: UNITED LAUNCH ALLIANCE, L.L.C.

Inventor： Christopher L. Bridges ,  Bernard Friedrich Kutter ,  Frank C. Zegler

IPC: F02K9/60 ,  F02K9/44 ,  F02K9/56 ,  F02K9/42 ,  B64G1/40

CPC classification number: F02K9/60 ,  B64G1/401 ,  B64G1/402 ,  F02K9/42 ,  F02K9/44 ,  F02K9/56 ,  F02K9/566

Abstract: 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.

公开(公告)号：US11572851B2

公开(公告)日：2023-02-07

申请号：US16449229

申请日：2019-06-21

Applicant: Sierra Space Corporation

Inventor： Ryan C. Cavitt ,  Trevor P. Ormonde ,  Jake W. Carey ,  Patrick D. Satyshur ,  Christopher P. St. Clair ,  Scott M. Munson

IPC: F02K9/68 ,  F02K9/28 ,  F02K9/72 ,  F02K9/42 ,  F02K9/44 ,  F02K9/58

Abstract: Various embodiments of a vortex thruster system is described herein that is configured to create at least three discrete thrust levels. In some embodiments, the vortex thruster system is configured to decompose a monopropellant and deliver the decomposed monopropellant into a vortex combustion chamber for generating various thrust levels. In some embodiments, the vortex thruster system includes a secondary propellant valve configured to deliver a secondary propellant into the vortex combustion chamber containing decomposed monopropellant to create a high thrust level. Related systems, methods, and articles of manufacture are also described.

公开(公告)号：US11555471B2

公开(公告)日：2023-01-17

申请号：US16567049

申请日：2019-09-11

Applicant: Deutsches Zentrum fuer Luft- und Raumfahrt e.V.

Inventor： Markus Ortelt ,  Hermann Hald

IPC: F02K9/62 ,  F02K9/64 ,  F02K9/42 ,  F02K9/44 ,  F23R3/00 ,  F23R3/34 ,  F23R3/18 ,  F23R3/20

Abstract: The invention relates to a thrust chamber device comprising a thrust chamber with a thrust space having a first portion, a second portion adjacent thereto, and a third portion adjacent to the second portion, the thrust space being delimited in all three portions by an outer nozzle wall having an outer thrust space surface, which outer thrust space surface tapers in the first and second portion toward the third portion, widens in the third portion away from the second portion, and has a narrowest point at the transition from the second portion to the third portion, the first portion being delimited by an inner nozzle wall with an inner thrust space surface, which tapers toward the second portion, an annular combustion chamber being formed between the inner thrust space surface and the outer thrust space surface and extending over the first portion.

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

IPC: B64G1/40 ,  F02K9/50 ,  F02K9/58 ,  F02K9/44 ,  B64G5/00 ,  F02K9/60

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.

公开(公告)号：US11480135B2

公开(公告)日：2022-10-25

申请号：US15370443

申请日：2016-12-06

Applicant: Aleksandr Rudakov

Inventor： Aleksandr Rudakov

IPC: F02K9/44 ,  F02K9/97 ,  F02K9/42

Abstract: The invention is in the field of engine building technology and may be used in space technology or aviation. Liquid-propellant rockets with Laval nozzles are well known, and they have the following insufficiencies: (1) high fuel consumption rates, which lead to increased dimensions and engine weight and boosters; (2) a relatively low combustion efficiency, because the low mass of the combustion products are emitted into the environment; (3) the large length of the de Laval nozzles with increased expansion ratios increase the dimensions and the engine weight; (4) use of high temperature rocket propellants—combustion products—in the camera and de Laval nozzle. These insufficiencies suppress using liquid-propellant rockets in space technology. The goal of the invention is decreasing the influence of these insufficiencies and obtaining an engine with improved efficiency. The goal is achieved with the creation of an engine with the subsonic discharge of combustion products and the creation of a simple nozzle construction.

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

Inventor： Benoît Mathieu André Cingal ,  Philippe Becret ,  Mathieu Henry Raymond Triger

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.

公开(公告)号：US11112040B2

公开(公告)日：2021-09-07

申请号：US16052468

申请日：2018-08-01

Applicant: The Boeing Company

Inventor： Michael Stephen Sparks ,  Verbon Blake Sparks

IPC: F16L27/02 ,  F16L27/06 ,  F02K9/44

Abstract: A gimbal apparatus is disclosed, including a tubular envelope with a variable length between first and second rim structures. A rigid ring structure inside the tubular envelope is connected to diametrically opposite first and second portions of the first rim structure, and is connected to diametrically opposite first and second portions of the second rim structure. A spoke bisects the ring structure.

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

IPC: F02K9/52 ,  F02K9/95 ,  F02K9/44 ,  F02K9/46 ,  F02K9/48 ,  F02K9/42 ,  F02K9/50 ,  B64G1/40

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.

公开(公告)号：US10717550B1

公开(公告)日：2020-07-21

申请号：US15795724

申请日：2017-10-27

Applicant: United Launch Alliance, L.L.C.

Inventor： Frank Charles Zegler

IPC: B64G1/26 ,  B64G1/40 ,  F02K9/44 ,  B64G1/42 ,  B64G1/00

Abstract: A system and methods are provided for combining systems of an upper stage space launch vehicle for enhancing the operation of the space vehicle. Hydrogen and oxygen already on board as propellant for the upper stage rockets is also used for other upper stage functions. Specifically, gases from the propellant tanks, instead of being dumped overboard, are used as fuel and oxidizer to power an internal combustion engine that produces mechanical power for driving other elements including a generator for generation of electrical current, mechanical power for fluid pumps, and other uses. The exhaust gas from the internal combustion engine is also used directly in one or more vehicle thrusters.