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1. 发明授权

US07509851B1 Plasma arcjet tunnel segments and method of making same 失效
标题翻译：等离子弧焊隧道段及其制造方法
公开(公告)号：US07509851B1
公开(公告)日：2009-03-31
申请号：US11981468
申请日：2007-10-30
申请人： Eric E. Schmidt , Elias Wade Wilson
发明人： Eric E. Schmidt , Elias Wade Wilson
IPC分类号： G01M9/00
CPC分类号： G01M9/04
摘要： A plasma heated arcjet wind tunnel is provided with tunnel segments in the arc-constrictor. The tunnel segments are fabricated of two concentric discs, an outer disc and an inner disc, with a groove formed in an outer edge of the inner disc. The two concentric discs which fit snugly into one another and are joined at their welded interface by a straight and angled butt joint formed between an inner edge of the outer disc and an outer edge of the inner disc. The straight and angled butt joints can be welded by electron beam welding, laser welding, or friction stir welding.
摘要翻译：等离子加热的电弧喷气风洞在弧形压缩机中设有隧道段。隧道段由两个同心盘，一个外盘和一个内盘制成，在内盘的外边缘形成一个槽。两个同心圆盘彼此紧密地配合，并且通过形成在外盘的内边缘和内盘的外边缘之间的直的和倾斜的对接接头在它们的焊接界面处接合。可以通过电子束焊接，激光焊接或摩擦搅拌焊接来焊接直线和倾斜的对接。

2. 发明授权

US10920714B2 Stable hybrid rocket technology 有权
公开(公告)号：US10920714B2
公开(公告)日：2021-02-16
申请号：US14212974
申请日：2014-03-14
申请人： Exquadrum, Inc.
发明人： Kevin E. Mahaffy , Byron Henning , Korey Robert Kline , Philip Pelfrey , Eric Schmidt , Elias Wilson
IPC分类号： F02K9/52 , F02K9/34 , F02K9/97 , F02K9/72
摘要： A hybrid rocket engine is described that achieves stable, highly efficient hybrid combustion by having a core flow of fuel-rich gas generator gases, with the flow being surrounded with an annular injection of oxidizer. The fuel-rich gas serves to vaporize and decompose the oxidizer, such as nitrous oxide, and prepare it for effective, stable combustion. In one embodiment, this is done at the head-end of a combustion chamber. The combustion products can then be expanded through a nozzle to create thrust. The engine can be an upper stage engine that can include modular thrust chambers and an integrated aerospike nozzle. The thrust chambers can be arranged in an array that rings the top of the aerospike nozzle.

3. 发明授权

US09791249B2 Kinetic fireball incendiary munition 有权
公开(公告)号：US09791249B2
公开(公告)日：2017-10-17
申请号：US14828918
申请日：2015-08-18
申请人： Exquadrum, Inc.
发明人： Robert L Geisler , Kevin E Mahaffy
IPC分类号： F42B12/44 , F42B12/58 , F42B12/52
CPC分类号： F42B12/44 , F42B12/52 , F42B12/58
摘要： A kinetic fireball incendiary munition is provided having an outer shell or bomb casing, one or more incendiary sub munitions therein, and an igniter therefore. Each of the submunitions includes an incendiary portion, at least one rocket motor that propels the submunition inside of a target volume, and an oxidizer for the incendiary portion and rocket motor. The submunitions liberate sufficient heat to produce elevated temperatures inside of a target structure to thermalize the contents thereof without creating a substantial overpressure or explosive effect.

4. 发明申请

US20160032867A1 STABLE HYBRID ROCKET TECHNOLOGY 审中-公开
标题翻译：稳定的混合式摇篮技术
公开(公告)号：US20160032867A1
公开(公告)日：2016-02-04
申请号：US14212974
申请日：2014-03-14
申请人： Exquadrum, Inc.
发明人： Kevin E. MAHAFFY , Byron HENNING , Korey Robert KLINE , Philip PELFREY , Eric Schmidt , Elias Wilson
IPC分类号： F02K9/24 , F02K9/97 , F02K9/52 , F02K9/34
CPC分类号： F02K9/52 , F02K9/34 , F02K9/72 , F02K9/97
摘要： A hybrid rocket engine is described that achieves stable, highly efficient hybrid combustion by having a core flow of fuel-rich gas generator gases, with the flow being surrounded with an annular injection of oxidizer. The fuel-rich gas serves to vaporize and decompose the oxidizer, such as nitrous oxide, and prepare it for effective, stable combustion. In one embodiment, this is done at the head-end of a combustion chamber. The combustion products can then be expanded through a nozzle to create thrust. The engine can be an upper stage engine that can include modular thrust chambers and an integrated aerospike nozzle. The thrust chambers can be arranged in an array that rings the top of the aerospike nozzle.
摘要翻译：描述了一种混合火箭发动机，其通过具有富燃料气体发生器气体的核心流动来实现稳定，高效的混合燃烧，其中气流被环形注入的氧化剂包围。富含燃料的气体用于蒸发和分解氧化剂，例如一氧化二氮，并将其制备用于有效，稳定的燃烧。在一个实施例中，这在燃烧室的前端进行。然后可以通过喷嘴将燃烧产物膨胀以产生推力。发动机可以是上级发动机，其可以包括模块化推力室和集成的空气喷嘴。推力室可以排列成环状空气喷嘴的顶部的阵列。

5. 发明授权

US08495959B2 Kinetic fireball incendiary munition 有权
标题翻译：动力火球燃烧弹药
公开(公告)号：US08495959B2
公开(公告)日：2013-07-30
申请号：US12748795
申请日：2010-03-29
申请人： Robert L Geisler , Kevin E Mahaffy
发明人： Robert L Geisler , Kevin E Mahaffy
IPC分类号： F42B12/44
CPC分类号： F42B12/44 , F42B12/52 , F42B12/58
摘要： A kinetic fireball incendiary munition is provided having an outer shell or bomb casing, one or more incendiary submunitions therein, and an igniter therefore. Each of the submunitions includes an incendiary portion, at least one rocket motor that propels the submunition inside of a target volume, and an oxidizer for the incendiary portion and rocket motor. The submunitions liberate sufficient heat to produce elevated temperatures inside of a target structure to thermalize the contents thereof without creating a substantial overpressure or explosive effect. The incendiary portion includes a solid propellant and, optionally, one or more energetic materials selected from the group consisting of phosphorous, boron, magnesium, aluminum, Fluorinert™-aluminum and BKNO3. The incendiary submunition may be in the shape of a ball or a circular disk with a rocket motor therein. The circular disk-shaped incendiary munition is provided with an outer layer of an insulation which is bonded to the propellant/incendiary material. A portion of the insulation on the top and bottom of the disk is weakened so as to break away when the top and bottom surfaces are ignited. In place of the rocket motor, the submunition may incorporate one or more barrels embedded in the incendiary material with a powder charge and projectile in each barrel. Ignition of the incendiary material results in detonation of the powder charge which propels projectiles radially outwardly and upwardly causing damage to containers of chemical/biological materials.
摘要翻译：提供了一种动力火球燃烧弹药，其中具有外壳或炸弹外壳，其中包括一个或多个燃烧子弹药和点火器。每个子弹药包括燃烧部分，至少一个将目标体积内的子弹药推进的火箭发动机，以及用于燃烧部分和火箭发动机的氧化剂。子弹药释放足够的热量以在目标结构内产生升高的温度，以使其内容物热化，而不产生显着的超压或爆炸效应。燃烧部分包括固体推进剂和任选的一种或多种选自磷，硼，镁，铝，氟化铝 - 铝和BKNO 3的高能材料。燃烧的子弹药可以是其中具有火箭发动机的球或圆盘的形状。圆形盘状燃烧弹药具有与推进剂/燃烧材料结合的绝缘层的外层。盘顶部和底部的绝缘部分被削弱，以便在顶部和底部表面被点燃时脱落。代替火箭发动机，子弹药可以将一个或多个嵌入在燃烧材料中的桶与每个桶中的粉末装料和抛射体混合。燃烧材料的点火导致粉末装料的爆炸，其将径向向外和向上推动射弹，导致对化学/生物材料的容器的损坏。

6. 发明授权

US11629669B1 Liquid monopropellant controlled solid rocket motor with aft end injection deflector 有权
公开(公告)号：US11629669B1
公开(公告)日：2023-04-18
申请号：US16831025
申请日：2020-03-26
申请人： EXQUADRUM, INC.
发明人： Kevin E. Mahaffy , Marlow Moser
IPC分类号： F02K9/52 , F02K9/97 , F02K9/26 , F02K9/72 , F02K9/82 , F02K9/42 , F02K9/80
摘要： A solid rocket motor is described that includes a solid propellant section, a nozzle, and a source of monopropellant, such as liquid monopropellant. The monopropellant is used to control various operational parameters of the solid rocket motor, such as thrust vector control, roll control, extinguishment of the motor, and cooling of the nozzle and/or nozzle throat. The nozzle and the nozzle throat can be an integrated, single piece assembly that facilitates re-use of the nozzle.

7. 发明授权

US09423224B2 Kinetic fireball incendiary munition 有权
标题翻译：动力火球燃烧弹药
公开(公告)号：US09423224B2
公开(公告)日：2016-08-23
申请号：US13929313
申请日：2013-06-27
申请人： Exquadrum, Inc.
发明人： Robert L Geisler , Kevin E Mahaffy
IPC分类号： F42B12/44 , F42B12/58 , F42B12/52
CPC分类号： F42B12/44 , F42B12/52 , F42B12/58
摘要： A kinetic fireball incendiary munition is provided having an outer shell or bomb casing, one or more incendiary sub munitions therein, and an igniter therefore. Each of the submunitions includes an incendiary portion, at least one rocket motor that propels the submunition inside of a target volume, and an oxidizer for the incendiary portion and rocket motor. The submunitions liberate sufficient heat to produce elevated temperatures inside of a target structure to thermalize the contents thereof without creating a substantial overpressure or explosive effect.
摘要翻译：提供了一种动力火球燃烧弹药，具有外壳或炸弹外壳，其中包括一个或多个燃烧弹药，因此也提供点火器。每个子弹药包括燃烧部分，至少一个将目标体积内的子弹药推进的火箭发动机，以及用于燃烧部分和火箭发动机的氧化剂。子弹药释放足够的热量以在目标结构内产生升高的温度，以使其内容物热化，而不产生显着的超压或爆炸效应。

8. 发明授权

US09021893B2 High survivability fluid flow sensor having a load cell for detecting loading on the sensor probe 有权
标题翻译：高生存性流体流量传感器具有负载传感器，用于检测传感器探头上的负载
公开(公告)号：US09021893B2
公开(公告)日：2015-05-05
申请号：US13710107
申请日：2012-12-10
申请人： Exquadrum, Inc.
发明人： Eric Schmidt , Elias Wilson , Landon Stevens , Lior Inberg
IPC分类号： G01F1/28 , G01P5/02 , G01P5/04
CPC分类号： G01F1/28 , G01P5/02 , G01P5/04
摘要： A high survivability fluid flow sensor includes a sensor housing defining an interior space. A sensor probe has a first end disposed within the interior space. The sensor probe also includes a second end opposite the first end outside the interior space. At least one load cell is disposed within the interior space and is operatively engaged with the first end of the sensor probe. The load cell is configured to detect loading on the sensor probe as a result of fluid flow impinging on the sensor probe adjacent to the second end. The sensor is operable to capture fluid flow data history through an over pressure event via the sensor probe, which exerts pressure upon the piezoelectric load cell(s), thereby enabling analysis of the wave fluid dynamics.
摘要翻译：高生存性流体流量传感器包括限定内部空间的传感器壳体。传感器探头具有设置在内部空间内的第一端。传感器探头还包括与内部空间外部的第一端相对的第二端。至少一个称重传感器设置在内部空间内并且与传感器探针的第一端可操作地接合。测力传感器被配置为检测由于流体流动撞击邻近第二端的传感器探头而在传感器探头上的负载。传感器可操作以通过传感器探针通过过压事件来捕获流体流动数据历史，传感器探针对压电负载传感器施加压力，从而能够分析波浪流体动力学。

9. 发明授权

US08164213B2 Orbital track wind turbine 失效
标题翻译：轨道式风力发电机
公开(公告)号：US08164213B2
公开(公告)日：2012-04-24
申请号：US12508127
申请日：2009-07-23
申请人： Kevin E. Mahaffy , Eric E. Schmidt , Ricky Howard , Byron Henning
发明人： Kevin E. Mahaffy , Eric E. Schmidt , Ricky Howard , Byron Henning
IPC分类号： F03D9/00 , H02P9/04 , F03B9/00
CPC分类号： F03D3/005 , F03D5/04 , F03D7/06 , F03D9/25 , F03D15/00 , F05B2240/214 , Y02E10/70 , Y02E10/74
摘要： An orbital track wind turbine for generation of electrical energy from wind power is provided. The wind turbine includes a plurality of spaced vertical supports to which at least two parallel spaced circular tracks are fixedly secured. These circular tracks are coaxial with one another and are positioned in parallel horizontal planes. A plurality of trucks extend between the circular tracks, the trucks having at least two grooved rollers which partially surround the circular tracks and operate in rolling engagement therewith. A circular power takeoff ring is coaxial with said circular tracks, and the power takeoff ring is attached to the truck which is rotatable in a horizontal plane about its central axis. A plurality of vertical airfoils extends around the circular power takeoff ring, with each of the airfoils being attached to a truck and the power takeoff ring. One or more generators are connected to the power takeoff ring, thereby converting wind generated rotation of the power takeoff ring to electrical energy.
摘要翻译：提供了用于从风力发电产生电能的轨道式风力涡轮机。风力涡轮机包括多个间隔开的垂直支撑件，至少两个平行间隔开的圆形轨道被固定地固定到该支撑件上。这些圆形轨道彼此同轴并且位于平行的水平面中。多个卡车在圆形轨道之间延伸，卡车具有部分包围圆形轨道并与其滚动接合的至少两个凹槽滚子。圆形动力输出环与所述圆形轨道同轴，并且动力输出环附接到可在水平面上围绕其中心轴线旋转的卡车。多个垂直翼型件围绕圆形动力输出环延伸，每个翼型件连接到卡车和动力输出环。一个或多个发电机连接到动力输出环，从而将产生的功率输出环的旋转转换成电能。

10. 发明公开

US20240280068A1 SENSITIZING ROCKET PROPULSION ENGINE 审中-公开
公开(公告)号：US20240280068A1
公开(公告)日：2024-08-22
申请号：US18443061
申请日：2024-02-15
申请人： EXQUADRUM, INC.
发明人： Kevin E. Mahaffy , Mark Heiner
IPC分类号： F02K9/72
CPC分类号： F02K9/72
摘要： A rocket propulsion engine includes a propellant vessel, a sensitizer vessel, a combustion chamber, an exhaust nozzle, and a controllable sensitizer injector. The combustion chamber combusts combustible propellant received from the propellant vessel and the combustion gas produced therefrom is exhausted through the exhaust nozzle. When activated, the controllable sensitizer injector introduce sensitizer from the sensitizer vessel into the propellant vessel to form an explosive mixture of the combustible propellant and the sensitizer. A method of operating a rocket propulsion engine includes supplying a combustible propellant from the propellant vessel into the combustion chamber, combusting the combustible propellant within the combustion chamber, and exhausting combustion gas produced through the exhaust nozzle. The method also includes introducing the sensitizer from the sensitizer vessel into the propellant vessel to form an explosive mixture within the propellant vessel.

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