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公开(公告)号：WO2016182496A1
公开(公告)日：2016-11-17
申请号：PCT/SE2016/050415
申请日：2016-05-09
申请人： ECAPS AKTIEBOLAG
发明人： ANFLO, Kjell
CPC分类号： F02K9/95 , F02K9/52 , F02K9/68 , F05D2260/99
摘要： The present invention relates to an ignition system for a liquid propellant chemical rocket engine, which comprises a thermal-catalytic element (20) for initiating decomposition of the liquid propellant, and an electrical heater (30) for electrically preheating the thermal-catalytic element, wherein the thermal-catalytic element is thermally connected to the electrical heater, both of which are located in a flow path of the propellant, a rocket engine, and a preburner, respectively, comprising the ignition system, as well as a method of preheating a liquid propellant rocket engine using the system, and a spacecraft comprising such engine.
摘要翻译： 本发明涉及一种用于液体推进剂化学火箭发动机的点火系统，其包括用于引发液体推进剂分解的热催化元件（20）和用于电热预热热催化元件的电加热器（30） 其中所述热催化元件热连接到所述电加热器，它们都分别位于包括所述点火系统的所述推进剂，火箭发动机和预燃机的流动路径中，以及预热方法 使用该系统的液体推进剂火箭发动机，以及包括这种发动机的航天器。
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公开(公告)号：WO2021101568A1
公开(公告)日：2021-05-27
申请号：PCT/US2019/062788
申请日：2019-11-22
发明人： YARNOT, Vincent C. , STANLEY, Steven , URBAN, Garrett , JAKUBEK, Matthew T. , ARGUST, Ronald L.
摘要： A monopropellant thruster according to an exemplary aspect of the present disclosure includes, among other things, a first part having a catalyst bed, a thrust chamber, and a nozzle. The first part is integrally formed via a single additive manufacturing process. The thruster further includes a second part, which is a closeout. A method is also disclosed.
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公开(公告)号：WO2014129419A1
公开(公告)日：2014-08-28
申请号：PCT/JP2014/053611
申请日：2014-02-17
申请人： 三菱重工業株式会社
摘要： ロケットエンジンは、燃料流路３１～３９と触媒部５１とタービン１２と第１ポンプ１１と燃焼室２１とノズル２２とを具備する。燃料流路３１～３９は、炭化水素系の燃料が流通する。触媒部５１は、燃料流路３１～３９の途中に設けられ、燃料をガス化する。タービン１２は、ガス化された燃料で駆動される。第１ポンプ１１は、タービン１２の駆動により燃料を燃料流路３１～３９へ供給する。燃焼室２１は、燃料流路３１～３９から供給されたガス化された燃料と、酸化剤とを燃焼する。ノズル２２は、燃焼室２１の燃焼ガスを送出し、燃料流路３１～３９の一部と熱交換して冷却する。
摘要翻译： 火箭发动机设有燃料流路（31-39），催化剂部分（51），涡轮机（12），第一泵（11），燃烧室（21）和喷嘴（22）。 烃类燃料流过燃料流路（31-39）。 催化剂部分（51）设置在燃料流路（31-39）的中间，并使燃料气化。 涡轮（12）由气化燃料驱动。 第一泵（11）通过涡轮机（12）的驱动将燃料供应到燃料流路（31-39）。 燃烧室（21）燃烧从燃料流路（31-39）供给的气化燃料和氧化剂。 喷嘴（22）在燃烧室（21）中输送燃烧气体，并通过与部分燃料流路（31-39）的热交换来冷却。
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公开(公告)号：WO2022081759A1
公开(公告)日：2022-04-21
申请号：PCT/US2021/054850
申请日：2021-10-13
摘要： Various embodiments of a vortex thruster system is described herein that are configured to create at least three discrete thrust levels. In some embodiments, the vortex thruster system includes a catalyst bed configured to decompose a monopropellant at more than one flow rate and deliver the decomposed monopropellant into a vortex combustion chamber for generating various thrust levels. In some embodiments, the catalyst bed includes a screen assembly positioned within the inner chamber of the catalyst bed. The screen assembly can include alternating reactive screens and inert screens. The reactive screens can include a catalytic coating for assisting with decomposing the monopropellant, and the inert screens can provide structural support for the screen assembly. Related systems, methods, and articles of manufacture are also described.
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公开(公告)号：WO2019021234A1
公开(公告)日：2019-01-31
申请号：PCT/IB2018/055595
申请日：2018-07-26
申请人： MINOTTI, Angelo
发明人： MINOTTI, Angelo
IPC分类号： F02K9/42 , F03H99/00 , F02K99/00 , F02K9/62 , F02K9/44 , F02K9/52 , F02K9/68 , F05D2250/15 , F05D2250/25
摘要： A space propulsion system (1), having reduced sizes, is designed specifically for the application on miniaturised satellites, but it can be scaled easily based upon a wide range of sizes of the target vehicle, and it comprises: a combustion chamber (10) implemented by a cylindrical container (11) having cylindrical walls (13), a first end (12) provided with at least an injection duct (15) for a combustion agent, a fuel and/or a mixture thereof, for the injection according to a direction tangential to said cylindrical walls so as to induce a helical combustion path in the combustion chamber (10), a possible additional perpendicular injection duct (16) for a fuel or a combustion agent, and an opposite end (14) provided with a discharge duct (19) arranged according to a direction tangential to said cylindrical walls (13) so as to receive and direct said helical path, wherein the cylindrical walls in case have a deposition of catalytic material inside thereof, for accelerating the combustion reaction; and a supersonic nozzle (20), connected to said discharge duct (19) for discharging the combustion products in the combustion chamber.
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公开(公告)号：WO2016186566A1
公开(公告)日：2016-11-24
申请号：PCT/SE2016/050467
申请日：2016-05-20
申请人： ECAPS AKTIEBOLAG
发明人： ANFLO, Kjell
CPC分类号： F02K9/42 , B23K1/0018 , B23K1/19 , B23K2201/001 , B23K2203/08 , B23K2203/26 , F02K9/68 , F05D2230/237
摘要： The present invention relates to an electrical heater assembly (1) for liquid propellant chemical rocket engines, and more particularly to such heater assembly comprising a heating cable (30) and a heater support (10), wherein the heater support exhibits a groove (17) in which the cable is accommodated, and wherein the heating cable is attached to the support by means of brazing (40) and/or by means of an enclosing member, as well as a liquid propellant chemical rocket engine provided with the heater assembly.
摘要翻译： 本发明涉及一种用于液体推进剂化学火箭发动机的电加热器组件（1），更具体地涉及包括加热电缆（30）和加热器支架（10）的加热器组件，其中加热器支架呈现出一个凹槽（17 ），其中所述电缆被容纳在其中，并且其中所述加热电缆通过钎焊（40）和/或借助于封闭构件以及设置有所述加热器组件的液体推进剂化学火箭发动机附接到所述支撑件。
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公开(公告)号：WO2018231800A1
公开(公告)日：2018-12-20
申请号：PCT/US2018/037068
申请日：2018-06-12
发明人： MCDEVITT, Michael, Ryan , HITT, Darren, L. , LEE, Patrick , DIEZ, Sandra, Romero , GOLDEN, Alex , MONGEON, Kevin , WATTS, Jon , HANTSCHE, Lydia , SHEA, Matthew
摘要： Propulsion systems that generate thrust from pressure generated by thermally decomposing a chemical blowing agent (CBA). In some embodiments, the CBA decomposes exothermically such that once thermal decomposition has been initiated, the thermal decomposition continues without additional energy input. In some embodiments, the CBA is utilized in a digital-microthruster array containing microthrusters that can be individually activated to provide thrust. In some embodiments, a CBA may be stored in one or more CBA-storage chambers that can be individually activated to charge and/or recharge a pressure tank that stores gas from the CBA decomposition under pressure for providing thrust. These and other embodiments are disclosed. Such propulsion systems can be used for any of a variety of spacecraft, including micro- and nano-satellites. Corresponding methods of generating thrust are also disclosed.
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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
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。
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公开(公告)号：WO2013048271A1
公开(公告)日：2013-04-04
申请号：PCT/PT2012/000027
申请日：2012-07-05
摘要： The present invention in the field of mechanical engineering consists of an improved chemical propulsion system in which at least one of the reactants is stored in the liquid phase (10). The invention includes a conventional reaction chamber (1) and nozzle (2) and re¬ uses waste heat from the refrigeration of said reaction chamber and nozzle, transferred to, for example piping (5) containing reactant that is adjacent to them, in order to vaporize and pressurize said reactant (s) (11) in the reservoirs (3, 12). The reactant (s) are then fed, in gaseous phase to the reaction chamber (1), with their flow controlled by valves (4). The liquid and gaseous phases in each reservoir may be physically separated by a separation element (13). This invention presents a simpler constructive solution for chemical propulsion systems, and is applicable especially to liquid or hybrid rocket motors.
摘要翻译： 本发明在机械工程领域包括一种改进的化学推进系统，其中至少一种反应物储存在液相（10）中。 本发明包括常规的反应室（1）和喷嘴（2），并且将来自所述反应室和喷嘴的制冷的废热再次传送到例如包含与其相邻的反应物的管道（5） 以使所述储存器（3,12）中的所述反应物（11）蒸发和加压。 然后将反应物以气相进料到反应室（1），其流量由阀（4）控制。 每个储存器中的液相和气相可以由分离元件（13）物理分离。 本发明提出了一种用于化学推进系统的更简单的建设性解决方案，并且特别适用于液体或混合火箭发动机。
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公开(公告)号：WO01007773A1
公开(公告)日：2001-02-01
申请号：PCT/GB2000/002837
申请日：2000-07-26
CPC分类号： F02K9/74 , F02K9/68 , F05D2250/82
摘要： A micro air vehicle comprising fuel tank connected to a region adapted to decompose hydrogen peroxide, and a nozzle adapted to exit the decomposition products of hydrogen peroxide to provide thrust. Preferably provide a hydrocarbon fuel is used to consume oxygen from the decomposition of hydrogen peroxide. Also an engine comprising a tank adapted to contain hydrogen peroxide, a decomposition region/chamber suitable for decomposing hydrogen peroxide, a nozzle to accelerate the resulting decomposition products, and a turbofan located downstream of the exit of said nozzle, and located within a duct so as to provide propulsive thrust.
摘要翻译： 一种微型飞行器，其包括连接到适于分解过氧化氢的区域的燃料箱，以及适于将过氧化氢的分解产物排出以提供推力的喷嘴。 优选提供烃燃料用于从过氧化氢的分解中消耗氧气。 还有一种发动机，其包括适于含有过氧化氢的罐，适于分解过氧化氢的分解区/室，用于加速所得分解产物的喷嘴和位于所述喷嘴出口下游的涡轮风扇，并位于管道内 以提供推进力。
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