RU2013136261A - METHOD OF BALLISTIC MAINTENANCE OF FLIGHT OF SPACE VEHICLE - Google Patents

METHOD OF BALLISTIC MAINTENANCE OF FLIGHT OF SPACE VEHICLE Download PDF

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RU2013136261A
RU2013136261A RU2013136261/11A RU2013136261A RU2013136261A RU 2013136261 A RU2013136261 A RU 2013136261A RU 2013136261/11 A RU2013136261/11 A RU 2013136261/11A RU 2013136261 A RU2013136261 A RU 2013136261A RU 2013136261 A RU2013136261 A RU 2013136261A
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gas
mass
capacity
intake
determined
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RU2013136261/11A
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Russian (ru)
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RU2549582C2 (en
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Сергей Михайлович Афанасьев
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Открытое акционерное общество "Информационные спутниковые системы" имени академика М.Ф. Решетнёва"
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Abstract

Способ баллистического обеспечения полета космического аппарата, включающий измерения температуры и давления рабочего тела (РТ) - газа, отличающийся тем, что на каждом шаге определения массовых остатков РТ до отбора части РТ из емкости рабочей системы по уравнению состояния идеального газа определяют массу газа в приборной емкости постоянного объема, снабженной датчиками давления и температуры, делают отбор части РТ из емкости рабочей системы в заборную емкость постоянного объема, переводят отобранную часть РТ в общую емкость, состоящую из заборной и приборной емкостей, объем которой трансформирует РТ в идеальный газ, по уравнению состояния идеального газа определяют массу газа в общей емкости, и по прямой пропорциональной зависимости отношения массы к объему для заборной емкости и емкости рабочей системы определяют искомую массу РТ - газа.The method of ballistic support for the flight of a spacecraft, including measuring the temperature and pressure of the working fluid (RT) - gas, characterized in that at each step of determining mass residues of the RT before taking part of the RT from the tank of the working system, the mass of gas in the instrument tank is determined by the equation of state of an ideal gas constant volume, equipped with pressure and temperature sensors, make the selection of part of the RT from the capacity of the working system in the intake capacity of a constant volume, transfer the selected part of the RT to the total capacity, consisting From the intake and instrument containers, the volume of which transforms the RT into an ideal gas, the mass of gas in the total capacity is determined by the equation of state of the ideal gas, and the desired mass of RT - gas is determined by the direct proportional relationship between the mass to volume ratio for the intake tank and the capacity of the working system.

Claims (1)

Способ баллистического обеспечения полета космического аппарата, включающий измерения температуры и давления рабочего тела (РТ) - газа, отличающийся тем, что на каждом шаге определения массовых остатков РТ до отбора части РТ из емкости рабочей системы по уравнению состояния идеального газа определяют массу газа в приборной емкости постоянного объема, снабженной датчиками давления и температуры, делают отбор части РТ из емкости рабочей системы в заборную емкость постоянного объема, переводят отобранную часть РТ в общую емкость, состоящую из заборной и приборной емкостей, объем которой трансформирует РТ в идеальный газ, по уравнению состояния идеального газа определяют массу газа в общей емкости, и по прямой пропорциональной зависимости отношения массы к объему для заборной емкости и емкости рабочей системы определяют искомую массу РТ - газа. The method of ballistic support for the flight of a spacecraft, including measuring the temperature and pressure of the working fluid (RT) - gas, characterized in that at each step of determining mass residues of the RT before taking part of the RT from the tank of the working system, the mass of gas in the instrument tank is determined by the equation of state of an ideal gas constant volume, equipped with pressure and temperature sensors, make the selection of part of the RT from the capacity of the working system in the intake capacity of a constant volume, transfer the selected part of the RT to the total capacity, consisting From the intake and instrument containers, the volume of which transforms the RT into an ideal gas, the mass of gas in the total capacity is determined by the equation of state of the ideal gas, and the desired mass of RT - gas is determined by the direct proportional relationship between the mass to volume ratio for the intake tank and the capacity of the working system.
RU2013136261/11A 2013-08-01 2013-08-01 Ballistic support of spacecraft flight RU2549582C2 (en)

Priority Applications (1)

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RU2013136261/11A RU2549582C2 (en) 2013-08-01 2013-08-01 Ballistic support of spacecraft flight

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RU2013136261/11A RU2549582C2 (en) 2013-08-01 2013-08-01 Ballistic support of spacecraft flight

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RU2013136261A true RU2013136261A (en) 2015-02-10
RU2549582C2 RU2549582C2 (en) 2015-04-27

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2653266C2 (en) * 2016-10-10 2018-05-07 Публичное акционерное общество "Ракетно-космическая корпорация "Энергия" имени С.П. Королева" Working material feed system and the method of operation of the working material feed system

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RU2330794C2 (en) * 2006-01-10 2008-08-10 Борис Михайлович Солодов Spacecraft acceleration method
RU2324628C2 (en) * 2006-02-28 2008-05-20 Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" имени С.П. Королева" Method of condition diagnostics of fuel tank separator of displacing system of fuel supply to space object
US20090288390A1 (en) * 2008-05-23 2009-11-26 Thomas Clayton Pavia Simplified thrust chamber recirculating cooling system
US9970740B2 (en) * 2011-03-14 2018-05-15 Rocket Lab Usa, Inc. Viscous liquid monopropellant

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Effective date: 20200802