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公开(公告)号：WO2017082968A1
公开(公告)日：2017-05-18
申请号：PCT/US2016/038486
申请日：2016-06-21
Applicant: RAYTHEON COMPANY
Inventor： VILLARREAL, James Kendall , LANGHENRY, Mark T. , DANFORTH, Jeremy C.
CPC classification number: F02K9/97 , F02K9/18 , F02K9/95 , F41A1/00 , F41F3/04 , F41F3/0413 , F42B15/00 , F42B15/01 , F42B15/10 , F42B15/105 , F42B15/36
Abstract: A motor assembly (10) is provided for use with projectiles, such as munitions, having relatively low length to diameter ratios. The motor assembly has an aerospike nozzle (42) and a casing disposed about the aerospike nozzle, where interior aerospike volume contains propellant and where walls of both the cowl of the casing and of the aerospike nozzle jointly define a combustion chamber (90).
Abstract translation: 提供了一种电动机组件（10），用于具有相对低的长径比的射弹（例如弹药）。 该电机组件具有一个气塞喷嘴（42）和一个围绕气塞喷嘴设置的外壳，内部气塞体积含有推进剂，并且外壳的气罩和气塞喷嘴两者的壁共同限定燃烧室（90） / p>
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公开(公告)号：WO2010082971A3
公开(公告)日：2010-07-22
申请号：PCT/US2009/062849
申请日：2009-10-30
Applicant: RAYTHEON COMPANY , LOEHR, Richard D. , TURNER, Gerald M. , DANFORTH, Jeremy C.
Inventor： LOEHR, Richard D. , TURNER, Gerald M. , DANFORTH, Jeremy C.
IPC: F02K9/08
Abstract: There is disclosed a solid fuel rocket motor including a center-perforated solid fuel grain. The solid fuel grain may be adapted to burn outwardly from a center surface facing the center perforation when ignited by a primary igniter during a normal mode of operation. The solid fuel grain may be further adapted to burn longitudinally from an end face when ignited by a secondary igniter during a safety mode of operation.
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公开(公告)号：WO2018034795A1
公开(公告)日：2018-02-22
申请号：PCT/US2017/043418
申请日：2017-07-22
Applicant: RAYTHEON COMPANY
Inventor： VILLARREAL, James K. , DANFORTH, Jeremy C. , SUMMERS, Matt H. , JOHNSON, Daniel K. , LANGHENRY, Mark T.
CPC classification number: F02K9/95 , C06B23/00 , C06B27/00 , C06B29/00 , C06B45/10 , F02K9/08 , F02K9/94
Abstract: Microwave energy is used to ignite and control the ignition of electrically operated propellant to produce high-pressure gas. The propellant includes conductive particles that act as a free source of electrons. Incoming microwave energy accumulates electric charge in an attenuation zone, which is discharged in the form of dielectric breakdowns to create local randomly oriented currents. The propellant also includes polar molecules. The polar molecules in the attenuation zone absorb microwave energy causing the molecules to rapidly vibrate thereby increasing the temperature of the propellant. The increase in temperature and the local current densities together establish an ignition condition to ignite and sustain ignition of an ignition surface of the attenuation zone as the zone regresses without igniting the remaining bulk of the propellant.
Abstract translation: 微波能量用于点燃和控制电动推进剂的点火以产生高压气体。 推进剂包括充当电子自由源的导电粒子。 输入的微波能量在衰减区累积电荷，衰减区以介质击穿形式放电，产生局部随机取向电流。 推进剂还包括极性分子。 衰减区中的极性分子吸收微波能量，使分子快速振动，从而增加推进剂的温度。 温度升高和局部电流密度一起形成点火条件，以点燃和维持衰减区的点火表面点火，因为区域退化而不点燃剩余的推进剂体积。
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公开(公告)号：WO2017176311A1
公开(公告)日：2017-10-12
申请号：PCT/US2016/056387
申请日：2016-10-11
Applicant: RAYTHEON COMPANY
Inventor： KOEHLER, Frederick B. , DANFORTH, Jeremy C. , LYMAN, Ward D. , LANGHENRY, Mark T. , SUMMERS, Matt H. , PONTIUS, Paul E. , PAPE, Brian M. , STALLINGS, Jared D. , VILLARREAL, James K. , VILLARREAL, Thomas
Abstract: A thruster includes multiple segments of electrically-operated propellant, electrodes for igniting one or a few of the electrically-operated propellant segments at a time, and a propellant feeder for moving further propellant segments into engagement with the electrodes. The segments may be configured to provide equal increments of thrust, or different amounts of thrust. The segments may each include an electrically-operated propellant material surrounded by a sealing material, so as to keep the propellant material away from moisture and other contaminants (and/or the vacuum of space) before each individual segment is to be used. The thruster may be included in any of a variety of flight vehicles, for example in a small satellite such as a CubeSat satellite, for instance having a volume of about 1 liter, and a mass of no more than about 1.33 kg.
Abstract translation: 推进器包括多个电动推进剂段，用于一次点燃一个或几个电动推进剂段的电极，以及推进剂供给器，用于将另外的推进剂段移动到与 电极。 这些段可以被配置成提供相等的推力增量或不同的推力量。 这些区段可以各自包括由密封材料围绕的电操作推进剂材料，以便在每个单独的区段将被使用之前使推进剂材料远离湿气和其他污染物（和/或空间的真空）。 推进器可以包括在各种飞行器中的任何一种中，例如在诸如CubeSat卫星的小卫星中，例如具有大约1升的体积和不大于大约1.33kg的质量。
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公开(公告)号：WO2018022203A1
公开(公告)日：2018-02-01
申请号：PCT/US2017/036803
申请日：2017-06-09
Applicant: RAYTHEON COMPANY
Inventor： SUMMERS, Matt H. , VILLARREAL, James K. , LANGHENRY, Mark T. , DANFORTH, Jeremy C. , WALTER, John W.
Abstract: Electrical ignition of electrically operated propellant in a gas generation system provides an ignition condition at an ignition surface between a pair of electrodes that satisfies three criteria of a current density J that exhibits a decreasing gradient along an axis normal to an ignition surface, is substantially constant across the ignition surface and exceeds an ignition threshold at the ignition surface. These criteria may be satisfied by one or more of an angled electrode configuration, a segmented electrode configuration or an additive to the electrically operated propellant that modifies its conductivity. These configurations improve burn rate control and consumption of the available propellant and are scalable to greater propellant mass to support larger gas generation systems.
Abstract translation: 气体发生系统中的电操作推进剂的电点火在一对电极之间的点火表面处提供满足电流密度J的三个标准的点火条件，所述电流密度J表现出沿着法向轴的递减梯度 到点火表面，在整个点火表面上基本恒定并超过点火表面处的点火阈值。 这些标准可以通过改变其电导率的成角度的电极构造，分段电极构造或电动推进剂的添加剂中的一种或多种来满足。 这些配置提高了燃烧速率控制和可用推进剂的消耗，并且可扩展到更大的推进剂质量以支持更大的气体发生系统。
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Patent Agency Ranking
公开(公告)号：WO2012145063A1
公开(公告)日：2012-10-26
申请号：PCT/US2012/025555
申请日：2012-02-17
Applicant: RAYTHEON COMPANY , DANFORTH, Jeremy C. , LOEHR, Richard D. , MURPHY, Kevin P.
Inventor： DANFORTH, Jeremy C. , LOEHR, Richard D. , MURPHY, Kevin P.
IPC: F02C7/22
CPC classification number: F02K9/00 , B64C2201/042 , F02K9/42 , F02K9/425 , F02K9/50 , F02K9/52 , F02K9/68 , H02J7/00 , H02K7/1823
Abstract: A gas generator assembly includes a propellant chamber housing an amine based propellant. A reaction chamber is coupled with the propellant chamber. The reaction chamber includes a reaction chamber housing, and a porous reaction matrix within the reaction chamber housing. The reaction matrix includes a catalyzing agent, and the catalyzing agent is configured to non-combustibly catalyze the amine based propellant into one or more pressurized gases. An injector is in communication with the propellant chamber. The injector is configured to deliver the amine based propellant to the porous reaction matrix. A discharge nozzle is coupled with the reaction chamber and is configured to accelerate and discharge the one or more pressurized gases. In one example, the gas generator is coupled with one or more of an impulse turbine assembly and an electric generator to form a micro power unit.
Abstract translation: 气体发生器组件包括容纳胺基推进剂的推进剂室。 反应室与推进剂室结合。 反应室包括反应室壳体和反应室壳体内的多孔反应基质。 反应基质包括催化剂，并且催化剂被配置为不可燃地将胺基推进剂催化成一种或多种加压气体。 喷射器与推进剂室连通。 喷射器构造成将胺基推进剂输送到多孔反应基质。 排放喷嘴与反应室联接并且构造成加速和排出一个或多个加压气体。 在一个示例中，气体发生器与脉冲涡轮机组件和发电机中的一个或多个耦合以形成微动力单元。
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公开(公告)号：WO2017105586A1
公开(公告)日：2017-06-22
申请号：PCT/US2016/055229
申请日：2016-10-03
Applicant: RAYTHEON COMPANY
Abstract: A device (100) is provided. The device includes at least one SMM component (115, 120, 130) fabricated from a shape memory material (SMM). The SMM component is configured to change shape in response to receiving a stimulus. The SMM component is also configured to deploy from a device body (105) of the device allowing the device to change shape in an advantageous way. A method (1000) implemented by a device (100) is also provided. The method includes changing (1010) a shape of an SMM component (115, 120, 130) of the device in response to receiving a stimulus. The SMM component is fabricated from an SMM. The method also includes deploying (1015) the SMM component from a device body (105) of the device allowing the device to change shape in an advantageous way.
Abstract translation: 提供了一种设备（100）。 该装置包括由形状记忆材料（SMM）制造的至少一个SMM部件（115,120,130）。 SMM组件配置为响应接收刺激而改变形状。 SMM部件还被配置为从装置的装置主体（105）展开，允许装置以有利的方式改变形状。 还提供了由设备（100）实现的方法（1000）。 该方法包括响应于接收刺激而改变（1010）设备的SMM组件（115,120,130）的形状。 SMM组件是由SMM制造的。 该方法还包括从设备的设备主体（105）部署（1015）SMM组件，允许设备以有利的方式改变形状。
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公开(公告)号：WO2014077889A1
公开(公告)日：2014-05-22
申请号：PCT/US2013/034910
申请日：2013-04-02
Applicant: RAYTHEON COMPANY
Inventor： DANFORTH, Jeremy C. , BUTTIGIEG, Gavin , LUKOW, Brian J.
CPC classification number: F42B10/661 , F02K7/02 , F02K9/08 , F42B3/04
Abstract: A detonation thrust-producing device (10) includes an explosive (32) located in a recess (34) in an external surface of a body (16). Detonation of the explosive expels material out of the recess, providing thrust to the body in an opposite direction. A mass, such as a metal disk (58), may be placed blocking or covering the external opening. The body may be a part of a vehicle, such as an airborne projectile (12). The thrust-producing device may include multiple detonation motors arrayed around the body, capable of being individually or multiply detonated. Such thrust-producing devices may be used for attitude adjustment, steering, or other control of the flight of the projectile or other air vehicle. The detonation thrust-producing devices have the advantage of a faster-response time than propellant-based devices, and do not need the nozzles that are used with many propellant-based devices.
Abstract translation: 爆炸推力产生装置（10）包括位于主体（16）的外表面中的凹部（34）中的炸药（32）。 爆炸物的爆炸将材料排出凹槽，向相反方向的身体提供推力。 可以将诸如金属盘（58）的块放置成阻挡或覆盖外部开口。 身体可能是车辆的一部分，例如机载射弹（12）。 推力产生装置可以包括围绕身体排列的多个爆震电动机，能够单独或多次引爆。 这种推力产生装置可以用于姿态调节，转向或其他控制飞弹或其他空中飞行器的飞行。 爆炸推力产生装置具有比基于推进剂的装置更快的响应时间的优点，并且不需要与许多基于推进剂的装置一起使用的喷嘴。
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9.发明公开
公开(公告)号：EP2699780A1
公开(公告)日：2014-02-26
申请号：EP12774463.9
申请日：2012-02-17
Applicant: Raytheon Company
Inventor： DANFORTH, Jeremy C. , LOEHR, Richard D. , MURPHY, Kevin P.
IPC: F02C7/22
CPC classification number: F02K9/00 , B64C2201/042 , F02K9/42 , F02K9/425 , F02K9/50 , F02K9/52 , F02K9/68 , H02J7/00 , H02K7/1823
Abstract: A gas generator assembly includes a propellant chamber housing an amine based propellant. A reaction chamber is coupled with the propellant chamber. The reaction chamber includes a reaction chamber housing, and a porous reaction matrix within the reaction chamber housing. The reaction matrix includes a catalyzing agent, and the catalyzing agent is configured to non-combustibly catalyze the amine based propellant into one or more pressurized gases. An injector is in communication with the propellant chamber. The injector is configured to deliver the amine based propellant to the porous reaction matrix. A discharge nozzle is coupled with the reaction chamber and is configured to accelerate and discharge the one or more pressurized gases. In one example, the gas generator is coupled with one or more of an impulse turbine assembly and an electric generator to form a micro power unit.
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公开(公告)号：EP2342444A2
公开(公告)日：2011-07-13
申请号：EP09838547.9
申请日：2009-10-30
Applicant: Raytheon Company
Inventor： LOEHR, Richard D. , TURNER, Gerald M. , DANFORTH, Jeremy C.
IPC: F02K9/08
Abstract: There is disclosed a solid fuel rocket motor including a center-perforated solid fuel grain. The solid fuel grain may be adapted to burn outwardly from a center surface facing the center perforation when ignited by a primary igniter during a normal mode of operation. The solid fuel grain may be further adapted to burn longitudinally from an end face when ignited by a secondary igniter during a safety mode of operation.
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