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公开(公告)号：US20240159204A1
公开(公告)日：2024-05-16
申请号：US18314270
申请日：2023-05-09
Inventor： Lipeng Wang , Peiying Zhu , Chenlong Liu , Zhongyi Liu
IPC: F02K9/60
CPC classification number: F02K9/605 , B60K2015/03032
Abstract: The present invention relates to a reinforced bulging tank of a launch vehicle and a manufacturing method therefor. The tank is made of metal material with good plasticity. Firstly, the tank is manufactured by welding annealed plastic metal materials, wherein internal longitudinal reinforcing ribs and internal annular frames/annular plates of barrel sections are welded with a barrel section shell by a low energy laser welding method, and tank bottoms are progressively welded by a plurality of conical sections. Weldments are strengthened and formed through internal pressure bulging under the constraint of external tooling. The outer walls of the barrel sections are not radially deformed under the constraint of a plurality of small width metal rings, and the metal rings are not connected to each other axially. The strength of the materials can be greatly improved by a deep cooling bulging technology.
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公开(公告)号：US10082106B2
公开(公告)日：2018-09-25
申请号：US14760190
申请日：2014-01-10
Applicant: SNECMA
Inventor： Didier Vuillamy , Gérard Roz
CPC classification number: F02K9/60 , F02K9/40 , F02K9/46 , F02K9/605 , F02K9/64 , F02K9/972 , F05D2260/20 , F05D2260/205
Abstract: The invention relates to the aerospace field, and in particular to the field of vehicles propelled by rocket engines. In particular, the invention relates to a feed circuit (6) for feeding a rocket engine (2) at least with a first liquid propellant, the feed circuit including at least one first heat exchanger (18) suitable for being connected to a cooling circuit (17) for cooling at least one heat source in order to cool said heat source by transferring heat to the first propellant, and, in addition, downstream from said first heat exchanger, a branch passing through a second heat exchanger.
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公开(公告)号：US10071825B2
公开(公告)日：2018-09-11
申请号：US14990180
申请日：2016-01-07
Applicant: Embry-Riddle Aeronautical University, Inc.
Inventor： Balaji Sivasubramanian , Leander Paul , Sathya Gangadharan
CPC classification number: B64G1/402 , B64D37/005 , B65D15/00 , B65D90/52 , F02K9/605 , F17C2260/016 , F17C2270/0194
Abstract: This disclosure includes a hybrid magneto-active membrane, which can be used as part of a Magneto-active Propellant Management Device (MAPMD), to actively control free surface effects of liquid materials, such as fuels, and to reduce fuel slosh. The disclosed MAPMD merges aspects of a diaphragm membrane with a magneto-active inlay to control the membrane during in-flight conditions.
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公开(公告)号：US20180072436A1
公开(公告)日：2018-03-15
申请号：US15561636
申请日：2016-03-18
Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD.
Inventor： Keitaro ISHIKAWA , Taichi AOYAMA , Kiyoshi KINEFUCHI , Koichi OKITA , Wataru SARAE
CPC classification number: B64G1/402 , B64G1/40 , B64G1/401 , F02K9/605 , F17C3/04 , F17C9/00 , F17C13/008 , F17C13/088 , F17C2201/0109 , F17C2201/054 , F17C2201/056 , F17C2203/0629 , F17C2221/011 , F17C2221/012 , F17C2223/0161 , F17C2265/066 , F17C2270/0194 , F17C2270/0197 , Y02E60/321
Abstract: To provide a propellant tank such as a fuel tank and an oxidant tank for a spacecraft, the propellant tank discharging propellant such as liquid hydrogen and liquid oxygen accumulated therein toward a rocket engine by pressurizing an inside thereof by operating gas. The propellant tank includes a tank body that accumulates therein the propellant in a liquid state, and a holding container that is provided inside the tank body and disposed with a predetermined gap from an inner wall of the tank body, so that the propellant in a liquid state can be held therein, when the inside of the tank body is in a microgravity state or a zero-gravity state.
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公开(公告)号：US20170254296A1
公开(公告)日：2017-09-07
申请号：US15059884
申请日：2016-03-03
Applicant: Daniel Patrick Weldon , Kevin Patrick Weldon
Inventor： Daniel Patrick Weldon , Kevin Patrick Weldon
Abstract: According to one contemplated embodiment of the rocket engine invention, water is first pumped from a water tank through a rocket nozzle cooling heat exchanger wherein it is evaporated into said superheated steam. A generator supplies electricity to an electrolyzer that electrolyzes superheated steam into gaseous hydrogen and gaseous oxygen. The gaseous hydrogen and gaseous oxygen is employed for forming an annular curtain of secondary combustion in a divergent rocket engine. The secondary combustion gas surrounds a central thrust of combustion gas produced in an upstream combustion chamber by a primary injection of hydrogen/oxygen supplied from a liquid hydrogen tank and liquid oxygen tank. The rocket liquid hydrogen tank and liquid oxygen tank are pressurized by gaseous hydrogen and gaseous oxygen generated by the electrolyzer.
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Patent Agency Ranking
公开(公告)号：US20160047510A1
公开(公告)日：2016-02-18
申请号：US14780319
申请日：2014-03-26
Applicant: SNECMA , CENTRE NATIONAL D'ETUDES SPATIALES CNES
Inventor： Jean-Marie CONRARDY , Brice GONCALVES
IPC: F16L59/065 , F17C1/12 , F02K9/60
CPC classification number: F16L59/065 , F01D25/145 , F02K9/605 , F16L59/12 , F17C1/12 , Y02T50/675
Abstract: A device for thermally insulating a piece of equipment, the device including a block of thermal insulation having at least a first hole; a deformable cover made of a gastight material and surrounding the block of insulation so that the wall of the first hole is covered by the gastight cover while leaving open the ends of first hole, the cover defining, at the second end, a first opening that communicates with the first hole and a second opening that communicates with the space situated between the insulating block and the cover; and the first and second openings of the cover being closed in gastight manner with the inside of the cover under a partial vacuum.
Abstract translation: 一种用于对一件设备进行绝热的装置，所述装置包括具有至少第一孔的绝热块; 由气密材料制成并且围绕所述绝缘体块的可变形盖，使得所述第一孔的壁被所述气密盖覆盖，同时保持打开所述第一孔的端部，所述盖在所述第二端处限定第一开口，所述第一开口 与第一孔连通，第二开口与位于绝缘块和盖之间的空间连通; 并且盖部分的第一和第二开口在部分真空下以气密的方式与盖的内部封闭。
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公开(公告)号：US20150354505A1
公开(公告)日：2015-12-10
申请号：US14760175
申请日：2014-01-10
Applicant: SNECMA
Inventor： Didier VUILLAMY , Gérard ROZ
IPC: F02K9/60
CPC classification number: F02K9/60 , F02K9/40 , F02K9/46 , F02K9/605 , F02K9/64 , F02K9/972 , F05D2260/20 , F05D2260/205
Abstract: The invention relates to the aerospace field, and in particular to the field of vehicles propelled by rocket engines. In particular, the invention relates to a feed circuit (6) for feeding a rocket engine (2) at least with a first liquid propellant, the feed circuit including at least one buffer-tank (20) for said first liquid propellant and a first heat exchanger (18) that is incorporated in said buffer tank (20) and suitable for being connected to a cooling circuit (17) for cooling at least one heat source in order to cool said heat source by transferring heat to the first propellant.
Abstract translation: 本发明涉及航空航天领域，特别涉及由火箭发动机推进的车辆领域。 特别地，本发明涉及用于至少用第一液体推进剂供给火箭发动机（2）的进料回路（6），所述进料回路包括用于所述第一液体推进剂的至少一个缓冲罐（20）和第一液体推进剂 热交换器（18），其结合在所述缓冲罐（20）中并且适于连接到用于冷却至少一个热源的冷却回路（17），以便通过将热传递到第一推进剂来冷却所述热源。
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公开(公告)号：US08967545B2
公开(公告)日：2015-03-03
申请号：US13133591
申请日：2008-12-10
Applicant: Giulio Manzoni
Inventor： Giulio Manzoni
CPC classification number: B64G1/1021 , B64G1/26 , B64G1/402 , B64G1/66 , B64G2001/1028 , F02K9/605 , F02K99/00
Abstract: A microsatellite comprising a propulsion module for moving and/or pointing the microsatellite and an imaging device (100) mounted to the propulsion module. Furthermore there is a fuel supply (210) located within the imaging device (100).
Abstract translation: 一种微卫星，包括用于移动和/或指向微卫星的推进模块和安装到推进模块的成像装置（100）。 此外，存在位于成像装置（100）内的燃料供应（210）。
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公开(公告)号：US20140283936A1
公开(公告)日：2014-09-25
申请号：US14352536
申请日：2012-10-18
Applicant: ASTRIUM SAS
Inventor： Louis Dandaleix
CPC classification number: B29C67/0077 , B29C64/153 , B29C64/35 , B29C2071/0045 , B29C2071/022 , B33Y10/00 , B33Y80/00 , B64G1/402 , F02K9/605 , F05D2300/614 , F17C13/008 , F17C2201/0104 , F17C2201/0157 , F17C2221/08 , F17C2223/0153 , F17C2270/0194 , F17C2270/0197 , Y10T29/49826 , Y10T137/86348
Abstract: A device for expelling/containing a predetermined liquid. The device configured to be built into a liquid tank operable at low or zero gravity and comprising a unitary three-dimensional sponge structure. The sponge structure comprises a set of substantially wire-like elements that extend between a peripheral area of the sponge structure and an area for expelling/containing liquid. The wire-like elements are substantially oriented in the direction of flow of the fluid within the device. The wire-like elements are connected together by crosspieces and are arranged such that the capillary gradient is positive or zero in the direction of flow of the fluid from the peripheral area to the area for expelling/containing liquid.
Abstract translation: 用于排出/容纳预定液体的装置。 该装置被配置成内置在可在低重力或零重力下操作并且包括一体的三维海绵结构的液体罐中。 海绵结构包括在海绵结构的周边区域和用于排出/容纳液体的区域之间延伸的一组基本上线状的元件。 线状元件基本上在装置内的流体的流动方向上取向。 线状元件通过挡条连接在一起，并且布置成使得毛细管梯度在流体从周边区域流到排出/容纳液体的区域的流动方向上为正或零。
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公开(公告)号：US20110240801A1
公开(公告)日：2011-10-06
申请号：US13133591
申请日：2008-12-10
Applicant: Giulio Manzoni
Inventor： Giulio Manzoni
CPC classification number: B64G1/1021 , B64G1/26 , B64G1/402 , B64G1/66 , B64G2001/1028 , F02K9/605 , F02K99/00
Abstract: A microsatellite comprising a propulsion module for moving and/or pointing said microsatellite and an imaging device (100) mounted to said propulsion module. Furthermore there is a fuel supply (210) located within said imaging device (100).
Abstract translation: 一种微卫星，包括用于移动和/或指示所述微卫星的推进模块和安装到所述推进模块的成像装置（100）。 此外，存在位于所述成像装置（100）内的燃料供应（210）。
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