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1. 发明授权

US11204001B2 Liquid combustion concentric injector and ignitor 有权
公开(公告)号：US11204001B2
公开(公告)日：2021-12-21
申请号：US16385061
申请日：2019-04-16
申请人： Alan Lee Wooldridge
发明人： Alan Lee Wooldridge
IPC分类号： F02K9/00 , F02K9/52 , F02K9/95
摘要： A rocket engine pintle injector with optimized spray pattern and with integrated igniter design for providing construction simplicity, throttleable thrust, stop/start/restart capability, optimized operational combustion, and improved ignition combustion stability. A user can start, throttle, and stop the engine by moving the internal concentric injector sleeve forward and backward to cause the fuel/oxidizer to spray out of the pintle head at different flow rates. The concentric igniter can be deployed so that the hot gasses or spark produced are radially projected into the spray of fuel/oxidizer surrounding the igniter. Once the fuel/oxidizer spray has been ignited, the igniter is stopped and retracted to protect the device from the heat of the combustion chamber and is ready for redeployment and restart of the engine as needed. Thus, a versatile, fully integrated, and scalable device can be used to start, throttle, stop, and restart any size rocket engine during any mission phase from launch to return from space.

2. 发明授权

US10344712B2 Rocket motor assembly 有权
公开(公告)号：US10344712B2
公开(公告)日：2019-07-09
申请号：US15457238
申请日：2017-03-13
申请人： Martin Baker Aircraft Co. Ltd.
发明人： Stephen Ruff
IPC分类号： B64D25/10 , F02K9/80 , B64D25/12 , F02K9/00 , F02K9/34
摘要： A rocket motor assembly (3) for use with an aircraft ejection seat comprises a rocket motor (4) having a rocket motor housing (5) and an exhaust outlet (6-9) to permit exhaust gas to be output from the rocket motor (4) along a thrust vector. The rocket motor assembly (3) comprises a first rotational coupling (12) which is configured to rotationally couple a first part (13) of the rocket motor housing (5) to a support structure (10) and a releasable coupling (14) which is configured to releasably couple a second part (15) of the rocket motor housing (5) to the support structure (10). The releasable coupling (14) is configured to release the second part (15) of the rocket motor housing (5) to permit the rocket motor housing (5) to rotate about the rotational coupling (12) to change the angle of the thrust vector of exhaust gas output from the exhaust outlet (6-9).

3. 发明授权

US10267265B2 Method and device for monitoring a parameter of a rocket engine 有权
公开(公告)号：US10267265B2
公开(公告)日：2019-04-23
申请号：US15301496
申请日：2015-04-02
申请人： SAFRAN AIRCRAFT ENGINES
发明人： Antoine Romet , Serge Le Gonidec , Dimitri Malikov , Jonathan Gazagnes
IPC分类号： F02K9/00 , F02K9/56 , F02K9/96 , G06N3/04 , G05B23/02 , G05B19/048
摘要： An obtaining step for obtaining a measurement of the monitored parameter as measured by a sensor and corresponding to an operating point of the engine, the operating point being defined by at least one regulation parameter of the engine; an estimation step for estimating a value of the monitored parameter for this operating point on the basis of a regulated value or a filtered setpoint value of the at least one regulation parameter of the engine defining the operating point; a comparison step for comparing an error between the measurement of the monitored parameter and its estimate relative to at least one threshold determined on the basis of an uncertainty on the error evaluated for the operating point; and a notification step for sending a notification in the event of the at least one threshold being crossed.

4. 发明授权

US10077742B2 Technical trial method 有权
公开(公告)号：US10077742B2
公开(公告)日：2018-09-18
申请号：US15034662
申请日：2014-10-24
申请人： SAFRAN AIRCRAFT ENGINES
发明人： Serge Le Gonidec , Sebastien Reichstadt , Virgil Musta
IPC分类号： F02C9/00 , F02K9/00 , F02K9/96 , G01M15/14
CPC分类号： F02K9/96 , F02C9/00 , F02K9/00 , F05D2260/83 , G01M15/14
摘要： A technical test method for evaluating at least one operating parameter of a device over a sequence of a plurality of operating stages, each stage corresponding to a stable value of at least one operating setpoint of the device. The method including at least sampling values of the at least one operating parameter over time, filtering the sampled values in order to obtain a filtered signal for each operating parameter, calculating the variance of the sampled values for each operating parameter in a sampling window during the operating stage, calculating the absolute value of the time derivative of the filtered signal for each operating parameter, and changing the value of the at least one operating setpoint when, for each operating parameter, the variance of the sampled values and the absolute value of the time derivative of the filtered signal are less than respective predetermined lower thresholds.

5. 发明授权

US09347399B1 Laser ignition for liquid propellant rocket engine injectors 失效
标题翻译：液体推进剂火箭发动机喷油器的激光点火
公开(公告)号：US09347399B1
公开(公告)日：2016-05-24
申请号：US08988059
申请日：1997-12-10
申请人： William S. Brown , Glenn T. Bennett
发明人： William S. Brown , Glenn T. Bennett
IPC分类号： F02K9/00 , F02K9/95
CPC分类号： F02K9/00 , F02K9/95
摘要： A laser beam is utilized to ignite the fuel and oxidizer injected into a combustion chamber. An injector has a plurality of injector elements each injecting fuel and oxidizer into a flame holding zone adjacent the injector face plate where fuel and oxidizer are mixing at a rate to sustain flammability. The laser beam is introduced parallel to the injector face plate passing through the fuel and oxidizer mixing zones igniting the propellants. The propellants are ignited by having a laser beam tuned to a frequency to excite the oxidizer such that it will chemically combine with the fuel to form an ignition kernel in the flame holding zone. When a plurality of injector elements are ignited in this manner a controlled ignition process in the combustion chamber is achieved.
摘要翻译：激光束用于点燃注入燃烧室的燃料和氧化剂。喷射器具有多个喷射器元件，每个喷射器元件将燃料和氧化剂喷射到与喷射器面板相邻的火焰保持区域中，其中燃料和氧化剂以可燃性的速率混合。激光束平行于通过燃料的注射器面板引入，并且点燃推进剂的氧化剂混合区域。通过将激光束调谐到频率以激发氧化剂来点燃推进剂，使得其与燃料化学结合以在火焰保持区域中形成点火核。当以这种方式点燃多个喷射器元件时，实现了燃烧室中的受控点火过程。

6. 发明授权

US08713912B2 Solid propellant rocket motors employing tungsten alloy burst discs and methods for the manufacture thereof 有权
标题翻译：使用钨合金爆破片的固体推进剂火箭发动机及其制造方法
公开(公告)号：US08713912B2
公开(公告)日：2014-05-06
申请号：US12834289
申请日：2010-07-12
申请人： James H. Dupont , Sean J. Whitmarsh
发明人： James H. Dupont , Sean J. Whitmarsh
IPC分类号： F02G1/00 , F02K9/00 , F16K17/14
CPC分类号： F02K9/32 , F02K9/978 , F05D2230/22 , F05D2300/13 , Y10T29/49346 , Y10T137/1647
摘要： Embodiments of a solid propellant rocket motor are provided. In one embodiment, the solid propellant rocket motor includes a pressure vessel having a cavity therein, a solid propellant disposed within the cavity, a nozzle fluidly coupled to the cavity, and a tungsten alloy burst disc positioned proximate the nozzle. The tungsten alloy burst disc is configured to block gas flow through the nozzle when the tungsten alloy burst disc is intact and to fragment at a predetermined burst pressure. Embodiments of a method are further provided for manufacturing a burst disc. In one embodiment, the method comprises the step of forming a burst disc from a tungsten alloy. Embodiments of a burst disc are still further provided. In one embodiment, the burst disc includes an outer annular portion, and a central portion comprising a tungsten alloy.
摘要翻译：提供固体推进剂火箭发动机的实施例。在一个实施例中，固体推进剂火箭发动机包括其中具有空腔的压力容器，设置在空腔内的固体推进剂，与腔体流体耦合的喷嘴以及位于喷嘴附近的钨合金爆裂盘。当钨合金爆破盘完好并且以预定的爆破压力分裂时，钨合金爆裂盘被构造成阻挡通过喷嘴的气体流动。还提供了用于制造突发盘的方法的实施例。在一个实施例中，该方法包括从钨合金形成爆破盘的步骤。还提供了突发盘的实施例。在一个实施例中，爆破盘包括外部环形部分和包括钨合金的中心部分。

7. 发明授权

US08707676B2 Radial flow rapid prototyping rocket motors 有权
标题翻译：径流快速成型火箭发动机
公开(公告)号：US08707676B2
公开(公告)日：2014-04-29
申请号：US12072918
申请日：2008-02-28
申请人： Jerome K. Fuller
发明人： Jerome K. Fuller
IPC分类号： F02K9/28 , F02K9/00
CPC分类号： F02K9/28 , B33Y10/00 , B33Y80/00 , F02K9/10 , F02K9/26 , F02K9/72 , F05D2210/40 , F05D2250/611
摘要： A hybrid rocket motor is manufactured by photopolymerizing the solid fuel grain in a stereolithography method, wherein fuel grains in a plastic matrix are deposited in layers for building a solid fuel rocket body in three dimensions for improved performance and for a compact design, the hybrid rocket motor including radial channels for defining a desired burn profile including the oxidizer to fuel burn ratio.
摘要翻译：混合式火箭发动机是通过以立体光刻法将固体燃料颗粒光聚合制成的，其中塑料基质中的燃料颗粒以三层沉积以建立固体燃料火箭体，以提高性能和紧凑设计，混合火箭马达包括径向通道，用于限定包括氧化剂与燃料燃烧比的期望的燃烧轮廓。

8. 发明申请

US20140013724A1 ELECTROMAGNETIC THRUSTER 审中-公开
标题翻译：电磁推杆
公开(公告)号：US20140013724A1
公开(公告)日：2014-01-16
申请号：US14001232
申请日：2012-03-22
申请人： Guido P. Fetta
发明人： Guido P. Fetta
IPC分类号： F02K9/00
CPC分类号： F02K9/00 , B64G1/409 , F03H99/00
摘要： Systems and methods for electromagnetic thrusting are disclosed. An electromagnetic thrusting system includes an axially-asymmetric resonant cavity including a conductive inner surface, the resonant cavity adapted to support a standing electromagnetic (EM) wave therein, the standing EM wave having an oscillating electric field vector defining a z-axis of the resonant cavity. The resonating cavity lacks 2nd-axis axial symmetry. The standing EM wave induces a net unidirectional force on the resonant cavity.
摘要翻译：公开了用于电磁推力的系统和方法。电磁推力系统包括轴向非对称谐振腔，其包括导电内表面，谐振腔适于支撑其中的驻极性电磁波（EM）波，所述立体EM波具有限定谐振的z轴的振荡电场矢量腔。谐振腔缺少第二轴轴对称。立体EM波在谐振腔上引起净单向力。

9. 发明申请

US20130318943A1 ROCKET MOTOR COMBUSTION CHAMBER INJECTION HEAD 有权
标题翻译： ROCKET电机燃烧室注射头
公开(公告)号：US20130318943A1
公开(公告)日：2013-12-05
申请号：US13989081
申请日：2011-11-14
申请人： Dominique Jean Etienne Indersie , Julien Bachelet , Olivier Delahaye
发明人： Dominique Jean Etienne Indersie , Julien Bachelet , Olivier Delahaye
IPC分类号： F02K9/00
CPC分类号： F02K9/60 , F02K9/00 , F02K9/42 , F02K9/44 , F02K9/52
摘要： An injection head including an annular distribution cavity for distributing a propellant upstream from an injection plate supporting injectors. The cavity includes a multiply-perforated distribution grid distributing the propellant, which grid is coaxial with the distribution cavity and of a concave shape that projects into the distribution cavity, the grid being fastened to a dome of the cavity.
摘要翻译：一种注射头，其包括用于将喷射剂上游的喷射剂分配到支撑喷射器的注射板的环形分布腔。空腔包括分布推进剂的多孔分布格栅，该格栅与分配腔同轴并且突出到分布腔中的凹形，网格紧固到空腔的圆顶。

10. 发明授权

US08596038B2 Liquid propellant tank and vapor jet emitting device including same 有权
标题翻译：液体推进剂罐和包括其的蒸气喷射发射装置
公开(公告)号：US08596038B2
公开(公告)日：2013-12-03
申请号：US13039859
申请日：2011-03-03
申请人： Takayuki Yamamoto , Osamu Mori , Yoshihiro Kishino , Masayuki Tamura , Shohei Koga , Ryoji Imai
发明人： Takayuki Yamamoto , Osamu Mori , Yoshihiro Kishino , Masayuki Tamura , Shohei Koga , Ryoji Imai
IPC分类号： F02K9/00
CPC分类号： B64G1/402 , F02K9/42 , F02K9/605
摘要： A liquid propellant tank for storing a liquid propellant A and supplying vapor produced by evaporation of part of the liquid propellant A to an external location comprises a tank body for storing the liquid propellant A, and a plurality of holder plates arranged inside the tank body, around an axis L of the tank body. The holder plates cause the liquid propellant A to adhere to them by surface tension, thereby establishing, inside the tank body, a liquid propellant holding area LA in which the liquid propellant A is held and a gas accumulation area GA in which vapor produced by evaporation of part of the liquid propellant A accumulates. The tank body has a propellant inlet open into the liquid propellant holding area LA and a gas outlet open into the gas accumulation area GA.
摘要翻译：用于储存液体推进剂A并将部分液体推进剂A蒸发产生的蒸气的液体推进剂罐包括用于储存液体推进剂A的罐体和设置在罐体内部的多个保持板，围绕罐体的轴线L。保持板使液体推进剂A通过表面张力附着在其上，从而在罐体内形成保持液体推进剂A的液体推进剂保持区域LA，以及通过蒸发产生蒸气的气体积聚区域GA 部分液体推进剂A积聚。罐体具有通向液体推进剂保持区域LA的推进剂入口和通向气体积聚区域GA的气体出口。

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