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1. 发明申请

WO2021171988A1 ロケットエンジン用燃焼装置审中-公开
公开(公告)号：WO2021171988A1
公开(公告)日：2021-09-02
申请号：PCT/JP2021/004584
申请日：2021-02-08
申请人：株式会社ＩＨＩ
发明人：石川　康弘 , 石原　新史 , 森　初男
IPC分类号： F02K9/44 , F02K9/64
摘要：このロケットエンジン用燃焼装置（Ｃ）は、燃料と酸化剤とを燃焼反応させる燃焼室と、燃料及び酸化剤を燃焼室に噴射する噴射器（３Ａ，３Ｂ）と、燃焼反応で発生した燃焼ガスを外部に噴射するノズルスカート（５）と、ロケットエンジン用燃焼装置の振動等価回路における等価イナータンスを増加せるイナータンス増加部（２Ａ，２Ｂ）と、を備える。

2. 发明申请

WO2020181117A1 SPACECRAFT THERMAL AND FLUID MANAGEMENT SYSTEMS 审中-公开
公开(公告)号：WO2020181117A1
公开(公告)日：2020-09-10
申请号：PCT/US2020/021237
申请日：2020-03-05
申请人： MOMENTUS INC.
发明人： KOKORICH, Mikhail , SERCEL, Joel , MITCHELL, Aaron , MINSTER, Gedi , WILSON, Lee , WANG, Yuqi , SMALL, James
IPC分类号： B64G1/40 , F02K9/44
摘要： To manage propellant in a spacecraft, the method of this disclosure includes storing propellant in a tank as a mixture of liquid and gas; transferring the propellant out of the tank; converting the mixture of liquid and gas propellant into a single phase, where the single phase is either liquid or gaseous; and supplying the single phase of the propellant to a thruster.

3. 发明申请

WO2013033437A3 THERMAL PHASE SEPARATION 审中-公开
标题翻译：热相分离
公开(公告)号：WO2013033437A3
公开(公告)日：2013-05-10
申请号：PCT/US2012053196
申请日：2012-08-30
申请人： FIRESTAR ENGINEERING LLC , MUNGAS GREGORY
发明人： MUNGAS GREGORY
IPC分类号： F02K9/44 , B01D17/00 , F02K9/56
CPC分类号： F02K9/44 , B64G1/402 , F05D2260/20 , Y10T137/0391 , Y10T137/6416
摘要： A thermal variation source (318) (e.g., a heater or a heat sink) is used to induce a temperature gradient across an interior surface of a storage tank (302). The storage tank stores a working fluid (e.g., a fuel, and oxidizer, or a monopropellant) that may have pockets of gaseous-phase working fluid interspersed within liquid-phase working fluid, or vice versa. In the absence of gravity or other significant forces on the working fluid, the temperature gradient is sufficient to cause phase-separation of the working fluid and allow either the liquid-phase or the gaseous-phase working fluid to be withdrawn from the storage tank, as desired.
摘要翻译：使用热变化源（318）（例如，加热器或散热器）以引起横跨储罐（302）的内表面的温度梯度。储罐储存可能具有散布在液相工作流体内的气相工作流体的小袋的工作流体（例如，燃料和氧化剂，或单一推进剂），反之亦然。在工作流体上不存在重力或其他显着力的情况下，温度梯度足以引起工作流体的相分离并且允许液相或气相工作流体从储罐中排出，如预期的。

4. 发明申请

WO0239032A3 METHOD AND SYSTEM FOR DENSIFYING CRYOGENIC PROPELLANTS 审中-公开
标题翻译：用于使致冷剂推进剂变浓的方法和系统
公开(公告)号：WO0239032A3
公开(公告)日：2002-08-22
申请号：PCT/US0121895
申请日：2001-07-12
申请人： PHPK TECHNOLOGIES INC
发明人： HOOD CHARLES B
IPC分类号： F25J3/02 , B64G1/40 , B64G5/00 , C06D5/00 , F02K9/44 , F25J1/02 , F17C11/00
CPC分类号： B64G5/00 , B64G1/402
摘要： The present invention relates to methods and systems (100) for densifying liquids, specifically the densification of cryogenic propellants. A preferred system of the present invention subcools and densifies liquid propellants by utilizing a countercurrent gas or liquid flow. The countercurrent flow preferably utilizes a gas having a lower boiling point than the propellants. A packed tower may then be used, at or above atmospheric pressure, to introduce the countercurrent flow to the propellant. This methodology avoids the costs and problems associated with subatmospheric operation. A preferred embodiment is directed toward the densification of liquid oxygen and liquid hydrogen. Systems and methods of the present invention may also be used to densify other liquids in similar fashion.
摘要翻译：本发明涉及致密液体的方法和系统（100），特别是低温推进剂的致密化。本发明的优选系统通过利用逆流气体或液体流动使液体推进剂过冷和致密化。逆流优选利用沸点低于推进剂的气体。然后可以在大气压或高于大气压下使用填充塔将逆流引入推进剂。这种方法避免了与次大气压操作相关的成本和问题。一个优选的实施方案涉及液氧和液态氢的致密化。本发明的系统和方法也可用于以类似的方式致密化其他液体。

5. 发明申请

WO9303962A3 SATELLITE PROPULSION AND POWER SYSTEM 审中-公开
标题翻译：卫星推进和动力系统
公开(公告)号：WO9303962A3
公开(公告)日：1993-04-29
申请号：PCT/US9206593
申请日：1992-08-07
申请人： TRW INC
发明人： SACKHEIN ROBERT L , HOOK DALE L , JOSEPH GARY W
IPC分类号： B64G1/40 , B64G1/00 , B64G1/24 , B64G1/26 , F02K9/42 , F02K9/44 , F02K9/50 , F02K9/52 , F02K9/54 , F02K9/58 , F02K9/64 , F02K9/68 , B64G
CPC分类号： F02K9/42 , B64G1/007 , B64G1/242 , B64G1/26 , B64G1/401 , B64G1/402 , B64G1/406 , F02K9/50 , F02K9/52 , F02K9/54 , F02K9/58 , F02K9/64 , F02K9/68
摘要： In the preferred embodiment of the invention, a cooled bipropellant thruster (70) for controlling the on-orbit position and orientation of a spacecraft is provided. The cooled bipropellant thruster (70) uses a liquid fuel and liquid oxidizer. The liquid fuel is decomposed in a first chamber (72) with a catalytic bed of decomposition material (74) and produces at least one reaction gas, which flows to the second reaction chamber (90). The second reaction chamber (90) is heated by the reaction gas, but is cooled by liquid oxidizer flowing through cooling passages (92, 94, 98, and 102), which brings the oxidizer into a heat exchange relationship with the second reaction chamber (90). During the heat exchange relationship, heat is transferred from the second reaction chamber (90) to the oxidizer and the oxidizer transforms into a gas. The gaseous oxidizer is fed into a second reaction chamber (90) to secondarily react with the reaction gas.

6. 发明申请

WO2023034577A2 MICROFABRICATED MULTIEMITTER ELECTROSPRAY THRUSTERS 审中-公开
公开(公告)号：WO2023034577A2
公开(公告)日：2023-03-09
申请号：PCT/US2022/042468
申请日：2022-09-02
申请人： THE REGENTS OF THE UNIVERSITY OF CALIFORNIA
发明人： GAMERO-CASTANO, Manuel , CISQUELLA-SERRA, Albert , GALOBARDES-ESTEBAN, Marc
IPC分类号： F03H1/00 , F02K9/44 , H01J27/02 , B64G1/40 , H01L21/302 , F02K9/42 , F02K9/60 , F02K9/80 , B64G1/405 , F03H1/0012
摘要： Microfabricated multiemitter electrospray thrusters in accordance with embodiments of the invention are disclosed. In one embodiment, an electrospray thruster for electrospraying at least one liquid propellant is provided, the electrospray thruster comprising: an emitter electrode comprising a backside comprising at least one microfluidic channel, wherein the at least one microfluidic channel provides hydraulic impedance to flow of the at least one liquid propellant, and a front side comprising an emitter array comprising at least one emitter, wherein the at least one emitter comprises an inner channel and an emitter tip; wherein the at least one liquid propellant reaches the emitter tip through the inner channel; and wherein each channel of the at least one microfluidic channel feeds the at least one liquid propellant to the at least one emitter via a hole connecting the at least one microfluidic channel with the inner channel of the at least one emitter.

7. 发明申请

WO2022108197A1 열교환 구조를 포함하는 연소기 및 이를 포함하는 로켓 审中-公开
公开(公告)号：WO2022108197A1
公开(公告)日：2022-05-27
申请号：PCT/KR2021/015864
申请日：2021-11-04
申请人： 한국항공우주연구원
发明人： 이금오 , 임병직 , 박순영
IPC分类号： F02K9/64 , F02K9/44
摘要： 본 발명은 열교환 구조를 포함하는 연소기 및 이를 포함하는 로켓에 관한 발명이다. 본 발명의 일 실시예에 따른 연소기는 이너 월, 상기 이너 월의 외측면을 커버하도록 배치되는 아우터 자켓, 상기 이너 월과 상기 아우터 자켓 사이에 배치되며, 연료 탱크에서 유입된 연료가 유동하는 복수 개의 제1 열교환 채널 및 상기 이너 월과 상기 아우터 자켓 사이에 배치되며, 가압 기체 탱크에서 유입된 가압 기체가 유동하는 제2 열교환 채널을 포함한다.

8. 发明申请

WO2018078579A1 SPACECRAFT ENGINE FUEL SPRAY-VALVE WITH A HEAT CONTROL SYSTEM 审中-公开
标题翻译：带有热控制系统的航天发动机燃油喷雾阀
公开(公告)号：WO2018078579A1
公开(公告)日：2018-05-03
申请号：PCT/IB2017/056691
申请日：2017-10-27
申请人： UAB "NANOAVIONIKA"
发明人： BUZAS, Vytenis
IPC分类号： F02K9/68 , F02K9/44
CPC分类号： F02K9/68 , F02K9/00 , F02K9/44 , F02K9/52
摘要： This description presents the design of propellant valve-injector of a spacecraft thruster with a heat (thermal) control system. The valve-injector consists of: the actuator for moving the valve in order to open and close the orifice of the propellant to the decomposition chamber; the needle closing/opening the said orifice; the housing integrating all parts of the valve-injector, and having the O-shaped sealing ring, elements performing the protective filter and other functions; the heat control system consisting of the heat sink element and the thermal barrier to ensure the proper temperature of the propellant supply system and the propellant contained therein, and the protection against overheating. The essence of the invention - technical solution eliminating the passage volume (pipeline) between the propellant supply control valve and the decomposition chamber, ensures the precision supply of propellant to the decomposition chamber at the uniform pressure (during the entire pulse). This increases the thruster controllability, as well as more efficient propellant use. The injector is easily integrated with spacecraft thruster.
摘要翻译：
本说明介绍了具有热（热）控制系统的航天器推进器的推进剂阀门喷射器的设计。该阀注射器包括：致动器，用于移动阀门以打开和关闭推进剂的孔口到分解室; 针关闭/打开所述孔口; 壳体集成了阀门喷射器的所有部件，并具有O形密封环，执行保护过滤器和其他功能的元件; 由散热器元件和热障组成的热控制系统，以确保推进剂供应系统和其中所含推进剂的适当温度，并防止过热。本发明的实质 - 消除推进剂供给控制阀和分解室之间的通道容积（管道）的技术方案确保了在均匀压力下（在整个脉冲期间）将推进剂精确地供应到分解室。这增加了推进器的可控性，以及更有效的推进剂使用。喷油器很容易与航天器推进器结合。

9. 发明申请

WO2017062335A1 FLEX JOINT HAVING LINER WITH ARTICULATED JOINT 审中-公开
标题翻译：具有连接接头的FLEX接头
公开(公告)号：WO2017062335A1
公开(公告)日：2017-04-13
申请号：PCT/US2016/055267
申请日：2016-10-04
申请人： AEROJET ROCKETDYNE, INC.
发明人： CIPRA, Dale
IPC分类号： F02K9/44 , F02K9/60 , F02K9/84
CPC分类号： F02K9/60 , F02K9/44 , F02K9/84
摘要： A flex joint (22) includes a bellows (33) and a liner system (46) disposed in the bellows. The liner system includes two generally cylindrical liner pieces (50,52) that are connected to each other in an articulated joint (54). One of the two generally cylindrical liner pieces defines a ball joint end (56) and the other of the two generally cylindrical liner pieces defines a socket joint end (58). The ball joint end is engaged with the socket joint end to form a ball and socket joint as the articulated joint.
摘要翻译：柔性接头（22）包括波纹管（33）和设置在波纹管中的衬垫系统（46）。衬垫系统包括在铰接接头（54）中彼此连接的两个大致圆柱形的衬垫件（50,52）。两个大致圆柱形的衬套中的一个限定了球接头端部（56），并且两个大致圆柱形的衬套中的另一个限定了插座接头端部（58）。球窝接头端与插座接合端接合，形成铰接接头的球窝接头。

10. 发明申请

WO2015176190A1 PULSDETONATIONSANTRIEB 审中-公开
标题翻译：脉冲爆震DRIVE
公开(公告)号：WO2015176190A1
公开(公告)日：2015-11-26
申请号：PCT/CH2015/000077
申请日：2015-05-18
申请人： EXPLO ENGINEERING AG
发明人： RÜEGG, Hans
IPC分类号： F23R7/00 , F02K7/02 , F02K7/06 , F02K1/08 , F02B71/06 , F02K9/58 , F02K9/44 , F02K9/52
CPC分类号： F02K7/06 , F02B71/06 , F02K1/08 , F02K1/15 , F02K7/02 , F02K9/44 , F02K9/52 , F02K9/58 , F02K9/86 , F02K9/97 , F05D2220/323 , F05D2220/80 , F05D2240/35 , F05D2250/41 , F23R7/00
摘要： Eine Vorrichtung dient zum wiederholten Erzeugen von Explosionen. Sie weist auf: einen Explosionsraum (11), eine Zufuhrleitung zum Zuführen eines fliessfähigen explosionsfähigen Materials, eine Ablassöffnung zum gerichteten Ablassen eines durch Zündung des explosionsfähigen Materials im Explosionsraum (11) erzeugten Gasdrucks, und ein bewegliches Verschlusselement (21, 31) zum teilweisen oder gänzlichen Verschliessen der Ablassöffnung (17). Dabei weist die Vorrichtung eine Austrittsdüse (15) mit einer Düseneintrittsfläche (13) und einer Düsenaustriltsfläche (14) auf, sowie eine Stelleinrichtung (23). Die Stelleinrichtung (23) ist dazu ausgebildet, nach einem Öffnen der Ablassöffnung (17) und einem Ausströmen von Explosionsgasen durch die Austrittsdüse (15) ein Flächenverhältnis zwischen der Düseneintrittsfläche (13) und der Düsenaustrittsfläche (14) einzustellen, welches mindestens annähernd einem idealen Flächenverhältnis zur Erzeugung einer maximalen Austrittsgeschwindigkeit der Explosionsgase in Abhängigkeit des Drucks im Explosionsraum (11) folgt.
摘要翻译：一种装置，用于重复地生成爆炸。它包括：一个爆炸腔室（11），用于提供可流动的爆炸材料，一个排出口，用于的定向放电通过在爆炸腔室中的爆炸材料的点火的供应管线（11）的气体压力产生的，和一个可移动封闭元件（21，31），用于部分地或说出关闭所述排气口（17）。在这种情况下，该装置包括一出口喷嘴（15），其具有喷嘴入口表面（13）和一个Düsenaustriltsfläche（14），和调节装置（23）。调节装置（23）适于，当排出口（17）和通过所述排气喷嘴（15）的爆炸气体的排放开口，以调节所述喷嘴入口面（13）和喷嘴出口区域（14）之间的区域比率，其中至少大约一个理想的面积比如下，以产生在爆炸室（11）中的压力的依赖性的爆炸气体的最大出口速度。

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