-
公开(公告)号：US20240263599A1
公开(公告)日：2024-08-08
申请号：US18497442
申请日：2023-10-30
申请人： PHASE FOUR, INC.
摘要： Systems and methods for a multimode propulsion system (MMPS) are presented. The MMPS includes a chemical thruster, an electric thruster, and a shared propellant tank. The MMPS further includes a propellant decomposition chamber that transforms, via a catalytic and/or electrolytic process, the propellant from the tank into vapor form for use as gas propellant by the electric thruster. The electric thruster can be configured for targeted ionization of one or more constituent species present in the vapor form of the propellant. Flow activation/control from the tank to the chemical and electric thrusters is provided by a fluidic feed system. The branches include a check valve and a pressure regulator in series connection. A normally closed squib valve prevents propellant flows/leaks from the tank to either the chemical or the electric thrusters when the MMPS is not in operation.
-
公开(公告)号：US12049855B1
公开(公告)日：2024-07-30
申请号：US18639030
申请日：2024-04-18
摘要： A method and apparatus for reducing consequences of a bulkhead failure for a liquid methane and liquefied oxygen rocket in which the rocket has a body, an oxygen tank positioned in the body, a fuel tank positioned in the body, at least one rocket engine positioned adjacent an end of the body, a bulkhead formed in the body between the oxygen tank and the fuel tank, and a container having triethylaluminum therein. The rocket engine is adapted to mix oxygen from the oxygen tank with fuel from the fuel tank. The container of triethylaluminum is positioned between the bulkhead and the fuel tank. The fuel tank will contain liquefied natural gas therein. The oxygen tank contains liquid oxygen.
-
公开(公告)号：US11920543B2
公开(公告)日：2024-03-05
申请号：US18129245
申请日：2023-03-31
摘要： Rocket propulsion systems and associated methods are disclosed. A representative system includes a combustion chamber having an inwardly-facing chamber wall enclosing a combustion zone. The chamber has a generally spherical shape and is exposed to the combustion zone. A propellant injector is coupled to the combustion chamber and has at least one fuel injector nozzle positioned to direct a flow of cooling fuel radially outwardly along the inwardly-facing chamber wall. In addition to or in lieu of the foregoing features, the injector can include an oxidizer piston and a fuel piston that deliver oxidizer and fuel, respectively, to the combustion chamber, in a sequenced manner so that the oxidizer is introduced prior to the fuel.
-
公开(公告)号：US11680544B1
公开(公告)日：2023-06-20
申请号：US17404666
申请日：2021-08-17
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.
-
公开(公告)号：US11643994B2
公开(公告)日：2023-05-09
申请号：US17133090
申请日：2020-12-23
摘要： Rocket propulsion systems and associated methods are disclosed. A representative system includes a combustion chamber having an inwardly-facing chamber wall enclosing a combustion zone. The chamber has a generally spherical shape and is exposed to the combustion zone. A propellant injector is coupled to the combustion chamber and has at least one fuel injector nozzle positioned to direct a flow of cooling fuel radially outwardly along the inwardly-facing chamber wall. In addition to or in lieu of the foregoing features, the injector can include an oxidizer piston and a fuel piston that deliver oxidizer and fuel, respectively, to the combustion chamber, in a sequenced manner so that the oxidizer is introduced prior to the fuel.
-
公开(公告)号：US20220381201A1
公开(公告)日：2022-12-01
申请号：US17769753
申请日：2020-10-16
摘要： A hybrid propulsion unit, for a space vehicle or rocket, includes an external body defining a combustion chamber configured to receive a block of solid propellant, a pressurized reservoir configured to receive a liquid propellant, and a nozzle to eject the combustion gases produced by the reaction of the propellants. The pressurized reservoir being placed inside the external body, surrounded by the block of solid propellant. The propulsion unit further includes a plurality of liquid-propellant injectors disposed axially between parts of the solid propellant to improve the efficacy of the combustion. A space vehicle, of the launch vehicle type, equipped with such hybrid propulsion unit.
-
公开(公告)号：US11498705B1
公开(公告)日：2022-11-15
申请号：US16871144
申请日：2020-05-11
发明人： Gordon C. Wu , Derek Chan , Suzan Q. Green
摘要： 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：US11491766B2
公开(公告)日：2022-11-08
申请号：US15250536
申请日：2016-08-29
发明人： Benjamin W. C. Garcia , Braden Day , Brian Christensen , David R. Nelson , Thomas Loveless , Elizabeth Bonderson
IPC分类号： B32B15/14 , B32B3/26 , F02K9/97 , F02K9/76 , B32B7/04 , B32B9/04 , B32B15/09 , B32B15/08 , B32B5/30 , B32B15/088 , B32B15/085 , B32B7/02 , B32B9/00 , B32B15/082 , B32B5/06 , B32B27/28 , B32B27/42 , B32B27/36 , B32B27/06 , B32B5/02 , B32B5/16 , B32B5/22 , B32B27/34 , B32B15/18 , B32B15/092 , B32B27/30 , B32B15/20 , B32B15/098 , B32B15/095 , B32B27/32 , B32B27/38 , F02K9/60 , B32B3/08 , B32B27/40
摘要： A hybrid metal composite (HMC) structure comprises tiers comprising fiber composite material structures, and additional tiers longitudinally adjacent one or more of the tiers and comprising perforated metallic structures and additional fiber composite material structures laterally adjacent the perforated metallic structures. Methods of forming an HMC structure, and related rocket motors and multi-stage rocket motor assemblies are also disclosed.
-
公开(公告)号：US11371468B2
公开(公告)日：2022-06-28
申请号：US16636234
申请日：2018-08-21
申请人： ARIANEGROUP SAS
IPC分类号： F02K9/56 , F02K9/50 , F02K9/60 , F16L55/052 , F02K9/44
摘要： 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：US20220090561A1
公开(公告)日：2022-03-24
申请号：US16948516
申请日：2020-09-22
发明人： Yen-Sen CHEN
摘要： A motor and fuel-powered hybrid system of a rocket thruster is disclosed, which mainly provides power through a motor and a fluid fuel injector. In particular, at the beginning stage of the rocket lift-off, the motor drives the compressor to provide power to send the rocket into air. When the speed and height of the rocket gradually increase, the fuel is ignited to give power to keep propelling the rocket, thereby reducing the fluid fuel that needs to be carried on the rocket, increasing the rocket's loading space and enhancing the carrying capacity.
-
-
-
-
-
-
-
-
-
搜索结果
299 条记录 (耗时 0.018 秒)
