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公开(公告)号：US20160237952A1
公开(公告)日：2016-08-18
申请号：US15031484
申请日：2014-10-21
申请人： SNECMA
CPC分类号： F02K9/58 , F02K9/425 , F02K9/50 , F02K9/605 , F05D2220/80
摘要： An autogenous pressurizer device for a main propellant tank, the device includes a pressurizer pipe connected to the main tank to inject propellant into the main tank, a pressurizer valve arranged on the pressurizer pipe, and a heater for heating the propellant upstream from the pressurizer valve. The pressurizer device includes a buffer tank connected to the pressurizer pipe upstream from the pressurizer valve.
摘要翻译： 一种用于主推进剂罐的自生加压装置，该装置包括连接到主罐的加压管，用于将推进剂喷入主罐中，加压阀布置在加压管上，加热器用于加热来自加压阀上游的推进剂 。 加压装置包括连接到加压阀上游的加压管的缓冲罐。
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公开(公告)号：US20160169159A1
公开(公告)日：2016-06-16
申请号：US14909945
申请日：2014-07-25
申请人： SNECMA
CPC分类号： F02K9/44 , F02K9/425 , F02K9/50 , F02K9/605 , F05D2220/80 , F05D2260/20
摘要： The device comprises a primary heater (58) suitable for heating the propellant coming from the tank (16) prior to it being reintroduced into its tank. The primary heater uses the heat of combustion from the engine (10) and the device further comprises a secondary heater (66) having its source of heat independent from the operation of the engine, the secondary heater being arranged downstream from the primary heater (58) in order to heat the propellant between its outlet from the primary heater and being reintroduced into the tank. The device also has means (62) between the feed to the primary heater (58) and the return of the propellant to the tank for putting the propellant under pressure.
摘要翻译： 该装置包括一个主加热器（58），适用于在其被重新引入其罐内之前加热来自罐（16）的推进剂。 主加热器使用来自发动机（10）的燃烧热，并且该装置还包括二次加热器（66），其二次加热器的热源独立于发动机的操作，二次加热器布置在主加热器（58）的下游 ），以便将推进剂在其来自主加热器的出口之间加热并重新引入罐中。 该装置还具有在进给到第一加热器（58）的进料和将推进剂返回到罐之间以将推进剂置于压力下的装置（62）。
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公开(公告)号：US20150211445A1
公开(公告)日：2015-07-30
申请号：US14607894
申请日：2015-01-28
申请人： Guido Kurth , Christoph Bauer
发明人： Guido Kurth , Christoph Bauer
摘要： Missile having a jet engine (2) comprising at least one turbine (3) and at least one compressing means (4), wherein gas generated in at least one gas generator (7) of the missile (1) drives a turbine (3). The compressing means (4) and the turbine (3) are arranged opposite to the flight direction (6) adjacent to each other.
摘要翻译： 具有喷射发动机（2）的导弹包括至少一个涡轮（3）和至少一个压缩装置（4），其中在导弹（1）的至少一个气体发生器（7）中产生的气体驱动涡轮机（3） 。 压缩装置（4）和涡轮机（3）相对于彼此相邻的飞行方向（6）布置。
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94.发明授权High specific impulse superfluid and nanotube propulsion device, system and propulsion method 有权高比冲冲超流体和纳米管推进装置，系统和推进方法公开(公告)号：US08991150B2
公开(公告)日：2015-03-31
申请号：US13560111
申请日：2012-07-27
摘要： A propulsion device including a chamber that stores a superfluid, a substrate coupled to a portion of the chamber, a plurality of orifices extending through the substrate, each of the plurality of orifices having a first end and a second end opposite the first end, the first end disposed in an interior of the chamber and the second end disposed outside the chamber; and a pressure source that generates a pressure differential between the first end of each of the plurality of orifices and the second end of each of the plurality of orifices.
摘要翻译： 一种推进装置，包括存储超流体的腔室，连接到腔室的一部分的基底，延伸穿过基底的多个孔口，多个孔口中的每一个孔具有与第一端相对的第一端和第二端， 第一端设置在腔室的内部，第二端设置在腔室的外部; 以及压力源，其在所述多个孔中的每一个的所述第一端和所述多个孔中的每一个的所述第二端之间产生压力差。
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公开(公告)号：US20130239544A1
公开(公告)日：2013-09-19
申请号：US13815002
申请日：2013-01-23
申请人： David B. Sisk , John M. Cramer
发明人： David B. Sisk , John M. Cramer
IPC分类号： F02K9/42
摘要： The present invention comprises a distributed system for providing warm, high pressure gas that is lighter weight, lower cost, and more reliable than comparable currant art pressurization systems. The invention employs Tridyne or another non-explosive but combustible pressurant mix flowing through a plurality of catalytic devices to provide heated pressurant to both the needed rocket system applications as well as to the plurality of pressurant storage bottles, thereby decreasing the mass of the unused pressurant at the end of mission.
摘要翻译： 本发明包括一种分布式系统，用于提供与可比较的醋栗艺术加压系统相比重量更轻，成本更低，更可靠的温暖高压气体。 本发明采用Tridyne或另一种非易燃但易燃的加压混合物，其流过多个催化装置以向所需的火箭系统应用以及多个加压储存瓶提供加热的加压，从而降低未使用的加压剂的质量 在任务结束时。
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公开(公告)号：US20090120060A1
公开(公告)日：2009-05-14
申请号：US10624754
申请日：2003-07-22
申请人： Keith Coste
发明人： Keith Coste
IPC分类号： F02K9/42
摘要： A catalytically activated transient decomposition propulsion system provides thrust by decomposing flow controlled propellant in contact with a catalyzing agent using a fixed volume of liquid propellant that is placed in contact with the catalyst within the decomposition chamber by a calibrated flow control valve. After injecting the liquid propellant into the decomposition chamber, the valve returns to the closed position while surface tension holds the liquid within the decomposition chamber until complete decomposition and exhaust of the warm gaseous products through a converging and diverging nozzle occurs. The increasing and decreasing transient pressure in the decomposition chamber changes each cycle in response to flow control valve actuation as the decomposition process is repeated.
摘要翻译： 催化活化的瞬时分解推进系统通过使用固定体积的液体推进剂分解与催化剂接触的流动控制推进剂来提供推力，其通过校准的流量控制阀与分解室内的催化剂接触。 在将液体推进剂注入分解室之后，阀返回到关闭位置，同时表面张力将液体保持在分解室内直到完全分解并且通过会聚和发散的喷嘴发生温热的气体产物的排出。 当分解过程重复时，分解室中的增加和减小的瞬态压力响应于流量控制阀致动而改变每个循环。
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公开(公告)号：US07124574B2
公开(公告)日：2006-10-24
申请号：US10309833
申请日：2002-12-04
申请人： Mark D. Horn , Shinjiro Miyata , Shahram Farhangi
发明人： Mark D. Horn , Shinjiro Miyata , Shahram Farhangi
CPC分类号： F02K9/52
摘要： A system to provide a two piece robust fluid injector. According to various embodiments, the fluid injector is a fuel injector for a combustion engine. The injector includes two coaxially formed annuluses. One annulus is formed in a face plate and the second annulus or hole is defined by a tube extending through the face plate. The tube extends through the face plate in a portion of a through bore which also is used to define the second annulus. The second annulus is formed using a throughbore through which the tube extends. This allows the second annulus to always be formed inherently and precisely substantially coaxial with the first annulus. Moreover, the second annulus can be formed with a much greater tolerance than if other independent components needed to be added.
摘要翻译： 一种提供两件式坚固流体注射器的系统。 根据各种实施例，流体喷射器是用于内燃机的燃料喷射器。 注射器包括两个同轴形成的环形物。 一个环形成在面板中，第二环或孔由延伸穿过面板的管限定。 管穿过通孔的一部分通过面板，该通孔也用于限定第二环。 第二环形物使用通孔穿过该管延伸。 这允许第二环总是与第一环空间固有地精确地基本上同轴地形成。 此外，与需要添加其他独立部件的情况相比，第二环可以具有更大的公差。
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公开(公告)号：US06952917B2
公开(公告)日：2005-10-11
申请号：US10610635
申请日：2003-07-02
申请人： Ryuichi Nagashima
发明人： Ryuichi Nagashima
摘要： The engine for a rocket is suitable for using for an educational program. The engine uses a liquid phase propellant having a predetermined boiling point and a heating substance having a temperature higher than the boiling point. The engine has an inner wall having a circumferential surface; an outer wall surrounding the inner wall, the outer wall having an interior surface spaced from the circumferential surface of the inner wall by a predetermined distance such that the space between the circumferential surface and the interior surface form a mixing chamber having an opening; and injector for injecting the liquid-phase propellant and the heating substance into the mixing chamber so that the propellant is evaporated by the heating substance thereby creating a jet stream moving from the opening of the mixing chamber to the outside of the mixing chamber.
摘要翻译： 用于火箭的发动机适用于教育程序。 发动机使用具有预定沸点的液相推进剂和具有高于沸点的温度的加热物质。 发动机具有具有圆周表面的内壁; 围绕所述内壁的外壁，所述外壁具有与所述内壁的周向表面间隔预定距离的内表面，使得所述圆周表面和所述内表面之间的空间形成具有开口的混合室; 以及用于将液相推进剂和加热物质注入到混合室中的喷射器，使得推进剂被加热物质蒸发，从而产生从混合室的开口移动到混合室的外部的喷射流。
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公开(公告)号：US06901740B2
公开(公告)日：2005-06-07
申请号：US10436140
申请日：2003-05-13
申请人： Max Calabro
发明人： Max Calabro
CPC分类号： F02K9/976 , F05D2240/1281
摘要： The pointed end of a central spike, used in an engine of a space launcher, may have a deformable structure that can adopt either a folded position or a deployed position.
摘要翻译： 在空间发射器的发动机中使用的中心尖头的尖端可以具有可以采用折叠位置或展开位置的可变形结构。
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公开(公告)号：US20050097883A1
公开(公告)日：2005-05-12
申请号：US10734279
申请日：2003-12-15
申请人： Chulsung Ryu , Wooseok Seol , Sangyeop Han
发明人： Chulsung Ryu , Wooseok Seol , Sangyeop Han
摘要： The present invention is related to an ablative baffle for a liquid rocket engine thrust chamber that comprises: a hub member having a hollow structure, of which both top and bottom parts are open; a plurality of blade rib members, each of which is connected removably at one end to the outer surface of the hub member; and a blade-connecting member having a hollow structure, of which both top and bottom parts are open, to the inner part of which each of blade rib members is connected at the other end. The present invention does not use a conventional internal cooling method, but an ablation cooling method using the composite heat resistant material structure with metal core, so that a liquid rocket engine system may be simplified, and the reliability of liquid rocket engine increases, and the manufacturing cost is cut down.
摘要翻译： 本发明涉及一种用于液体火箭发动机推力室的烧蚀挡板，其包括：具有中空结构的毂构件，其顶部和底部都是开放的; 多个叶片肋构件，每个叶片肋构件的一端可拆卸地连接到轮毂构件的外表面; 以及具有中空结构的叶片连接构件，其顶部和底部部分均敞开，在其内部，每个叶片肋构件在另一端连接。 本发明不使用传统的内部冷却方法，而是使用具有金属芯的复合耐热材料结构的消融冷却方法，从而可以简化液体火箭发动机系统，并且液体火箭发动机的可靠性增加， 制造成本下降。
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