RU2012121447A - METHOD FOR REGULATING THE OPERATION MODE OF A LIQUID ROCKET MOTOR UNIT - Google Patents

METHOD FOR REGULATING THE OPERATION MODE OF A LIQUID ROCKET MOTOR UNIT Download PDF

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Publication number
RU2012121447A
RU2012121447A RU2012121447/06A RU2012121447A RU2012121447A RU 2012121447 A RU2012121447 A RU 2012121447A RU 2012121447/06 A RU2012121447/06 A RU 2012121447/06A RU 2012121447 A RU2012121447 A RU 2012121447A RU 2012121447 A RU2012121447 A RU 2012121447A
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RU
Russia
Prior art keywords
regulating
liquid rocket
change
gas flow
operation mode
Prior art date
Application number
RU2012121447/06A
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Russian (ru)
Other versions
RU2499906C1 (en
Inventor
Анатолий Сергеевич Васин
Эдуард Владимирович Венгерский
Генрих Леонидович Усов
Михаил Иванович Ермолов
Валерий Юрьевич Рябых
Владимир Николаевич Кучкин
Original Assignee
Федеральное Государственное Унитарное Предприятие "Научно-Производственное Объединение "Техномаш"
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Application filed by Федеральное Государственное Унитарное Предприятие "Научно-Производственное Объединение "Техномаш" filed Critical Федеральное Государственное Унитарное Предприятие "Научно-Производственное Объединение "Техномаш"
Priority to RU2012121447/06A priority Critical patent/RU2499906C1/en
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Publication of RU2012121447A publication Critical patent/RU2012121447A/en
Publication of RU2499906C1 publication Critical patent/RU2499906C1/en

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  • Testing Of Engines (AREA)
  • Jet Pumps And Other Pumps (AREA)

Abstract

Способ регулирования режима работы жидкостной ракетной двигательной установки, заключающийся в изменении проходного сечения органа, регулирующего расход газа наддува в зависимости от кавитационного запаса давления насосов турбонасосного агрегата, измерение параметров двигателя и определение их производных по времени, отличающийся тем, что изменение проходного сечения органа, регулирующего расход газа наддува, устанавливают по величине производной изменения давления и температуры на входе в двигатель.The method of regulating the operating mode of a liquid rocket propulsion system, which consists in changing the flow area of the body regulating the charge gas flow depending on the cavitation pressure reserve of the pumps of the turbopump unit, measuring engine parameters and determining their derivatives in time, characterized in that the change in the flow area of the body regulating boost gas flow rate, set by the derivative of the change in pressure and temperature at the inlet to the engine.

Claims (1)

Способ регулирования режима работы жидкостной ракетной двигательной установки, заключающийся в изменении проходного сечения органа, регулирующего расход газа наддува в зависимости от кавитационного запаса давления насосов турбонасосного агрегата, измерение параметров двигателя и определение их производных по времени, отличающийся тем, что изменение проходного сечения органа, регулирующего расход газа наддува, устанавливают по величине производной изменения давления и температуры на входе в двигатель. The method of regulating the operating mode of a liquid rocket propulsion system, which consists in changing the flow area of the body regulating the charge gas flow depending on the cavitation pressure reserve of the pumps of the turbopump unit, measuring engine parameters and determining their derivatives in time, characterized in that the change in the flow area of the body regulating boost gas flow rate, set by the derivative of the change in pressure and temperature at the inlet to the engine.
RU2012121447/06A 2012-05-25 2012-05-25 Method to regulate mode of operation of liquid rocket propulsion system RU2499906C1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2012121447/06A RU2499906C1 (en) 2012-05-25 2012-05-25 Method to regulate mode of operation of liquid rocket propulsion system

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2012121447/06A RU2499906C1 (en) 2012-05-25 2012-05-25 Method to regulate mode of operation of liquid rocket propulsion system

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RU2012121447A true RU2012121447A (en) 2013-11-27
RU2499906C1 RU2499906C1 (en) 2013-11-27

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Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2622677C1 (en) * 2016-07-05 2017-06-19 Акционерное общество "Конструкторское бюро химавтоматики" Rps fuel component management system

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2524938A1 (en) * 1982-04-08 1983-10-14 Centre Nat Etd Spatiales METHOD FOR REGULATING THE MIXING RATIO OF PROPERGOLS FOR A LIQUID PROPERGOLS ENGINE BY MEASURING FLOW RATES AND REGULATORS FOR ITS IMPLEMENTATION
DE4005607C1 (en) * 1990-02-22 1991-07-25 Erno Raumfahrttechnik Gmbh, 2800 Bremen, De
RU2180704C2 (en) * 2000-03-06 2002-03-20 Федеральное государственное унитарное предприятие "НПО ТЕХНОМАШ" Method of control of mode of operation of liquid-propellant rocket engine plant
RU2180705C2 (en) * 2000-03-10 2002-03-20 Федеральное государственное унитарное предприятие "НПО ТЕХНОМАШ" Method of control of mode of operation of liquid-propellant rocket engine plant
RU2418188C1 (en) * 2010-03-17 2011-05-10 Федеральное Государственное Унитарное Предприятие "Научно-Производственное Объединение "Техномаш" Method of controlling rocket fluid-propellant engine operation

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Publication number Publication date
RU2499906C1 (en) 2013-11-27

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Effective date: 20160526