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1.发明授权Magnetic means for determining partial pressure of oxygen particularly in underwater breathing apparatus 失效用于确定氧分压的磁性方法，特别是在水下呼吸器中
公开(公告)号：US4173975A
公开(公告)日：1979-11-13
申请号：US875654
申请日：1978-02-06
CPC分类号： G01N27/74
摘要： A paramagnetic oxygen sensor wherein a reference chamber is oscillated into and out of an air gap of a magnetic circuit by means of a piezoelectric bender bar. The oscillating reference periodically displaces the ambient gas under measurement in the air gap and causes a varying flux in the magnetic circuit which is sensed, amplified and provided as an output signal indicative of the partial pressure of oxygen of the gas mixture.
摘要翻译： 顺磁性氧传感器，其中通过压电弯曲杆将参考室摆动进出磁路的气隙。 振荡基准周期性地使气隙中测量的环境气体移位，并且在磁路中引起变化的磁通，其被感测，放大并作为指示气体混合物的氧分压的输出信号提供。
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公开(公告)号：US07784269B1
公开(公告)日：2010-08-31
申请号：US11509905
申请日：2006-08-25
IPC分类号： F02K9/00
CPC分类号： F02K9/64
摘要： A propulsion system for a rocket engine and a method of cooling a rocket engine includes a propellant tank fluidically coupled to the rocket engine to hold a pressurized propellant, a coolant tank to hold a coolant, a first heat exchanger thermally coupled to the rocket engine and fluidically coupled to the coolant tank, a second heat exchanger thermally coupled to the propellant tank and fluidically coupled to the first heat exchanger, and a third heat exchanger disposed inside the propellant tank to thermally couple a propellant withdrawn from the tank for combustion to a propellant disposed inside the tank. The coolant flows from the coolant tank to the first heat exchanger and through the first heat exchanger to cool the rocket engine. The propellant withdrawn from the propellant tank receives heat from the propellant disposed inside the tank through the third heat exchanger to convert to a gaseous propellant when withdrawn from the propellant tank as a liquid propellant. The coolant flows from the first heat exchanger to the second heat exchanger and through the second heat exchanger to heat the propellant disposed inside the propellant tank.
摘要翻译： 用于火箭发动机的推进系统和冷却火箭发动机的方法包括流体耦合到火箭发动机的推进剂罐，以保持加压推进剂，冷却剂罐以保持冷却剂，热联接到火箭发动机的第一热交换器， 流体耦合到冷却剂箱，热耦合到推进剂罐并流体耦合到第一热交换器的第二热交换器和设置在推进剂罐内部的第三热交换器，以将从罐中取出的推进剂热联接到推进剂 置于水箱内。 冷却剂从冷却剂罐流到第一热交换器并通过第一热交换器冷却火箭发动机。 从推进剂罐中取出的推进剂通过第三热交换器从设置在罐内的推进剂中接收热量，以当作为液体推进剂从推进剂罐中取出时转化为气体推进剂。 冷却剂从第一热交换器流到第二热交换器，并通过第二热交换器加热设置在推进剂罐内的推进剂。
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公开(公告)号：US08341933B2
公开(公告)日：2013-01-01
申请号：US12846728
申请日：2010-07-29
IPC分类号： B63H11/00
CPC分类号： F02K9/64
摘要： A method of cooling a rocket engine that includes removal of a gaseous propellant from a tank containing liquid propellant, thereby cooling the propellant in the tank, cooling a rocket engine with a coolant, thereby heating the coolant, and transferring heat from the heated coolant into the propellant in the tank, thereby heating the propellant in the tank and maintaining the pressure in the tank. In certain embodiments, the coolant is injected into the rocket engine after transferring heat from the rocket engine to the propellant in the tank.
摘要翻译： 一种冷却火箭发动机的方法，包括从包含液体推进剂的罐中取出气体推进剂，从而冷却罐中的推进剂，用冷却剂冷却火箭发动机，从而加热冷却剂，并将热量从加热的冷却剂传递到 坦克中的推进剂，从而加热罐中的推进剂并维持罐中的压力。 在某些实施例中，在将热量从火箭发动机传递到罐中的推进剂之后，将冷却剂注入到火箭发动机中。
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公开(公告)号：US07854395B1
公开(公告)日：2010-12-21
申请号：US12029345
申请日：2008-02-11
IPC分类号： B64D33/04
CPC分类号： F02K9/64
摘要： The present invention relates to rocket engine combustion chambers, and more particularly to an improved rocket engine combustion chamber having a jacket. In some embodiments, a combustion system for a rocket engine includes an injector, a cylindrical combustion chamber, and a jacket coupled to the combustion chamber and to the injector. The combustion chamber can expand axially and/or radially with respect to the jacket. The outer surface of the combustion chamber includes a plurality of flow channels. One or more piston seals and/or bellows can be included to allow axial expansion of the combustion chamber with respect to the jacket. A gap formed between the inner surface of the jacket and the outer surface of the combustion chamber allows for radial expansion of the combustion chamber with respect to the jacket.
摘要翻译： 火箭发动机燃烧室技术领域本发明涉及火箭发动机燃烧室，更具体地涉及一种具有护套的改进的火箭发动机燃烧室。 在一些实施例中，用于火箭发动机的燃烧系统包括喷射器，圆柱形燃烧室和联接到燃烧室和喷射器的套管。 燃烧室可相对于护套轴向和/或径向膨胀。 燃烧室的外表面包括多个流动通道。 可以包括一个或多个活塞密封件和/或波纹管，以允许燃烧室相对于护套的轴向膨胀。 在护套的内表面和燃烧室的外表面之间形成的间隙允许燃烧室相对于护套的径向膨胀。
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公开(公告)号：US20100326044A1
公开(公告)日：2010-12-30
申请号：US12846728
申请日：2010-07-29
IPC分类号： F02K9/64
CPC分类号： F02K9/64
摘要： A coolant system for a rocket propulsion system having a rocket engine and a propellant tank includes a first heat exchanger that is operatively coupled to the rocket engine. The cooling system also includes a second heat exchanger that is operatively coupled to the propellant tank, a coolant tank that is configured to hold a coolant, and a pump. The cooling system also includes a flow circuit, through which the coolant flows with the aid of the pump. The flow circuit is defined by the pump, the first heat exchanger, the second heat exchanger and the coolant tank. The coolant is pumped by the pump from the coolant tank to the first heat exchanger. The heat of combustion from the rocket engine is transferred to the coolant to cool the rocket engine. The heated coolant transfers the heat therein to the propellant with the second heat exchanger, thereby causing a pressure of the propellant in the propellant tank to be maintained at a desired level.
摘要翻译： 用于具有火箭发动机和推进剂罐的火箭推进系统的冷却剂系统包括可操作地联接到火箭发动机的第一热交换器。 冷却系统还包括可操作地联接到推进剂罐的第二热交换器，被配置为保持冷却剂的冷却剂罐和泵。 冷却系统还包括流动回路，冷却剂借助于该循环泵借助泵流动。 流动回路由泵，第一热交换器，第二热交换器和冷却剂箱限定。 冷却剂被泵从冷却剂罐泵送到第一热交换器。 来自火箭发动机的燃烧热量被传送到冷却剂以冷却火箭发动机。 加热的冷却剂将热量传递到具有第二热交换器的推进剂，从而使推进剂罐中的推进剂的压力保持在期望的水平。
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公开(公告)号：US20100218482A1
公开(公告)日：2010-09-02
申请号：US11509905
申请日：2006-08-25
CPC分类号： F02K9/64
摘要： A propulsion system for a rocket engine and a method of cooling a rocket engine includes a propellant tank fluidically coupled to the rocket engine to hold a pressurized propellant, a coolant tank to hold a coolant, a first heat exchanger thermally coupled to the rocket engine and fluidically coupled to the coolant tank, a second heat exchanger thermally coupled to the propellant tank and fluidically coupled to the first heat exchanger, and a third heat exchanger disposed inside the propellant tank to thermally couple a propellant withdrawn from the tank for combustion to a propellant disposed inside the tank. The coolant flows from the coolant tank to the first heat exchanger and through the first heat exchanger to cool the rocket engine. The propellant withdrawn from the propellant tank receives heat from the propellant disposed inside the tank through the third heat exchanger to convert to a gaseous propellant when withdrawn from the propellant tank as a liquid propellant. The coolant flows from the first heat exchanger to the second heat exchanger and through the second heat exchanger to heat the propellant disposed inside the propellant tank.
摘要翻译： 用于火箭发动机的推进系统和冷却火箭发动机的方法包括流体耦合到火箭发动机的推进剂罐，以保持加压推进剂，冷却剂罐以保持冷却剂，热联接到火箭发动机的第一热交换器， 流体耦合到冷却剂箱，热耦合到推进剂罐并流体耦合到第一热交换器的第二热交换器和设置在推进剂罐内部的第三热交换器，以将从罐中取出的推进剂热联接到推进剂 置于水箱内。 冷却剂从冷却剂罐流到第一热交换器并通过第一热交换器冷却火箭发动机。 从推进剂罐中取出的推进剂通过第三热交换器从设置在罐内的推进剂中接收热量，以当作为液体推进剂从推进剂罐中取出时转化为气体推进剂。 冷却剂从第一热交换器流到第二热交换器，并通过第二热交换器加热设置在推进剂罐内的推进剂。
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公开(公告)号：US07900435B1
公开(公告)日：2011-03-08
申请号：US11752866
申请日：2007-05-23
IPC分类号： F02K9/00
CPC分类号： F02K9/52 , F05D2250/82
摘要： An improved coaxial injector for injecting first and second propellants into a combustion chamber of a rocket engine is provided. The injector includes a first plate, a second plate, a plurality of channels formed in the first plate, and a plurality of tubes extending through the second plate and into the plurality of channels. The tubes inject a first propellant, such as an oxidizer, into the combustion chamber, and the channels inject a second propellant, such as a fuel, around the tubes and into the combustion chamber.
摘要翻译： 提供了一种用于将第一和第二推进剂注入到火箭发动机的燃烧室中的改进的同轴喷射器。 喷射器包括第一板，第二板，形成在第一板中的多个通道，以及延伸穿过第二板并进入多个通道的多个管。 管将第一推进剂（例如氧化剂）注入燃烧室，并且通道在管周围注入第二推进剂（例如燃料）并进入燃烧室。
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公开(公告)号：US07784268B1
公开(公告)日：2010-08-31
申请号：US11499087
申请日：2006-08-04
IPC分类号： F02K9/00
CPC分类号： F02K9/46 , F02K9/343 , F02K9/40 , F02K9/563 , F05D2260/601
摘要： A system and method of driving a fuel pump and/or an oxidizer pump in a propulsion system includes pumping an oxidizer from an oxidizer supply to a rocket engine with the oxidizer pump. A first portion of the pumped oxidizer is used for combustion in the rocket engine. The heat from the combustion of the first portion of the oxidizer is then transferred to a second portion of the pumped oxidizer to convert the second portion of the oxidizer to a super-heated gaseous oxidizer. The super-heated gaseous oxidizer operates a motor, which drives the oxidizer pump and/or the fuel pump.
摘要翻译： 在推进系统中驱动燃料泵和/或氧化剂泵的系统和方法包括用氧化剂泵将氧化剂从氧化剂供应泵送到火箭发动机。 泵送的氧化剂的第一部分用于火箭发动机的燃烧。 氧化剂的第一部分的燃烧产生的热量然后转移到泵送的氧化剂的第二部分，以将氧化剂的第二部分转化成超加热的气体氧化剂。 过热气态氧化器操作电动机，其驱动氧化剂泵和/或燃料泵。
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