RU2014101385A - HYBRID ROCKET AND RECTANOUS AIR-REACTIVE AEROSPACE ENGINE - Google Patents
HYBRID ROCKET AND RECTANOUS AIR-REACTIVE AEROSPACE ENGINE Download PDFInfo
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- RU2014101385A RU2014101385A RU2014101385/06A RU2014101385A RU2014101385A RU 2014101385 A RU2014101385 A RU 2014101385A RU 2014101385/06 A RU2014101385/06 A RU 2014101385/06A RU 2014101385 A RU2014101385 A RU 2014101385A RU 2014101385 A RU2014101385 A RU 2014101385A
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Abstract
1. Гибридный ракетно-прямоточный воздушно-реактивный аэрокосмический двигатель, отличающийся тем, что включает ракетный двигатель (РД) на топливе в виде нанопорошка алюминия размером не более 25 нм в жидкой водной фазе, предназначенный для создания тяги при старте и на начальном этапе полета и для наработки топлива, потребляемого совмещенным с ним прямоточным воздушно-реактивным двигателем (ПВРД) крейсерского полета на молекулярном водороде, образующимся при сжигании нанопорошка алюминия, и характеризующийся тем, что содержит цилиндрическую обечайку, на одном конце которой вход для потока атмосферного воздуха, а на другом - выпускное сопло, центральное осесимметричное или клиновидное тело, на кромках которого реализуется система скачков уплотнения, размещенное в обечайке, камеру сгорания для сжигания нанопорошка алюминия в парах воды, являющуюся одновременно химическим реактором для получения водорода, размещенную в клиновидном теле, сопряженную с ним на выходе и с соплом, приспособленным к образованию зоны горения при взаимодействии истекающего из сопла водорода и поступающего воздушного потока.2. Гибридный ракетно-прямоточный воздушно-реактивный аэрокосмический двигатель по п.1, отличающийся тем, что в зоне горения молекулярный водород и окислитель находятся в стехиометрическом соотношении (отношение топливо/окислитель ϕ=1) либо образуют бедную смесь (соотношением ϕ<1).3. Гибридный ракетно-прямоточный воздушно-реактивный аэрокосмический двигатель по п.1 или 2, отличающийся тем, что работает на скорости, равной числу Маха М=0-24.4. Гибридный ракетно-прямоточный воздушно-реактивный аэрокосмический двигат1. A hybrid ramjet ramjet aerospace engine, characterized in that it includes a rocket engine (RD) in the form of aluminum nanopowder with a size of not more than 25 nm in the liquid aqueous phase, designed to create traction at launch and at the initial stage of flight for producing fuel consumed by a ramjet engine combined with it of a cruise flight on molecular hydrogen generated during the combustion of aluminum nanopowder, and characterized in that it contains a cylindrical a shell, at one end of which there is an inlet for atmospheric air flow, and at the other — an outlet nozzle, a central axisymmetric or wedge-shaped body, on the edges of which a system of shock waves is implemented, located in the shell, a combustion chamber for burning aluminum nanopowder in water vapor, which is simultaneously a chemical reactor for producing hydrogen, placed in a wedge-shaped body, coupled to it at the outlet and with a nozzle adapted to form a combustion zone during the interaction of hydrogen flowing from the nozzle and stepping potoka.2 air. The hybrid ramjet ramjet aerospace engine according to claim 1, characterized in that in the combustion zone molecular hydrogen and an oxidizing agent are in a stoichiometric ratio (fuel / oxidizer ratio ϕ = 1) or form a lean mixture (ratio ϕ <1) .3 . The hybrid ramjet ramjet aerospace engine according to claim 1 or 2, characterized in that it operates at a speed equal to the Mach number M = 0-24.4. Hybrid rocket-propelled air-propelled aerospace engine
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RU2014101385/06A RU2563641C2 (en) | 2014-01-17 | 2014-01-17 | Hybrid aerospace rocket ramjet |
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RU2014101385/06A RU2563641C2 (en) | 2014-01-17 | 2014-01-17 | Hybrid aerospace rocket ramjet |
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RU2014101385A true RU2014101385A (en) | 2015-07-27 |
RU2563641C2 RU2563641C2 (en) | 2015-09-20 |
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RU2014101385/06A RU2563641C2 (en) | 2014-01-17 | 2014-01-17 | Hybrid aerospace rocket ramjet |
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Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
RU180227U1 (en) * | 2017-11-02 | 2018-06-06 | Закрытое акционерное общество "Институт телекоммуникаций" | Combined three-mode jet engine |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
RU2647919C1 (en) * | 2016-06-20 | 2018-03-21 | Владимир Леонидович Письменный | Ramjet engine |
RU2633730C1 (en) * | 2016-10-31 | 2017-10-17 | Федеральное государственное автономное образовательное учреждение высшего образования "Национальный исследовательский Томский государственный университет" (ТГУ) | Method of working process organizing in direct-flow air jet engine |
CN107503862A (en) * | 2017-10-10 | 2017-12-22 | 北京航空航天大学 | A kind of hybrid rocket combination circulation propulsion system and its control method |
RU196907U1 (en) * | 2019-08-12 | 2020-03-19 | Владимир Анисимович Романов | Missile with a gas-vapor powder engine, explosive nuclear charges and a rotary nozzle |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
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DE1926728B1 (en) * | 1969-05-24 | 1971-03-25 | Messerschmitt Boelkow Blohm | Combustion chamber for jet engines, especially for rocket ramjet engines |
FR2564201B1 (en) * | 1984-05-15 | 1986-10-31 | Inst Prikladnoi Fiziki Akademi | DEVICE FOR THE CALIBRATION AND VERIFICATION OF THE MAGNETIC CONTROL MEANS OF FERROMAGNETIC PRODUCTS |
US4644746A (en) * | 1985-12-30 | 1987-02-24 | L. W. Fleckenstein, Inc. | Gas compressor for jet engine |
RU2280778C2 (en) * | 2004-07-23 | 2006-07-27 | Борис Федорович Кочетков | Method of and device for creating reactive thrust in form of combination air jet engine |
RU2439358C2 (en) * | 2009-11-05 | 2012-01-10 | Открытое акционерное общество "Корпорация "Тактическое ракетное вооружение" | Air ramjet engine operating on powder metal fluid |
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Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
RU180227U1 (en) * | 2017-11-02 | 2018-06-06 | Закрытое акционерное общество "Институт телекоммуникаций" | Combined three-mode jet engine |
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Effective date: 20210804 |