scholarly journals Outline of Liquid Rocket Propulsion System of H-IIA Launch Vehicle.

1998 ◽  
Vol 46 (535) ◽  
pp. 453-457
Author(s):  
Yukio FUKUSHIMA ◽  
Hiroyuki NAKATSUJI ◽  
Ryuuji NAGAO ◽  
Takashi MAEMURA ◽  
Keiichi HASEGAWA
Keyword(s):  
Launch Vehicle ◽  
Propulsion System ◽  
Rocket Propulsion ◽  
Liquid Rocket Propulsion ◽  
Liquid Rocket

FEASIBILITY ANALYSIS OF LIQUID PROPELLANT SETTLING IN THE TANKS OF A SPACE PROPULSION SYSTEM AFTER FLYING IN ZERO GRAVITY USING A SEPARATING TURN MANUEVER OF THE ORBITAL UNIT

2021 ◽  
pp. 78-87
Author(s):  
Nikolay N. TUPITSIN
Keyword(s):  
Attitude Control ◽  
Feasibility Studies ◽  
Propulsion System ◽  
Zero Gravity ◽  
Liquid Propellant ◽  
Propulsion Systems ◽  
Rocket Propulsion ◽  
Liquid Rocket Propulsion ◽  
Liquid Rocket ◽  
Main Engine

The paper presents results of preliminary design feasibility studies of using inertial settling of liquid propellant in tanks of space liquid rocket propulsion systems and separating from the propellant the ullage gases formed in zero gravity by means of centrifugal forces generated when the orbital unit performs the programmed turn maneuver proposed by the author. It shows that performing propellant settling and ullage gas separation by means of the separating turn maneuver makes it possible to significantly reduce propellant consumption in propulsion systems for attitude control and ullage engines. Key words: space liquid rocket propulsion system, main engine, separation of ullage gases from liquid propellant, separating turn maneuver of the orbital unit.

Feasibility analysis of liquid propellant settling in the tanks of a space propulsion system after flying in zero gravity using a separating turn maneuver of the orbital unit

2021 ◽  
pp. 78-87
Author(s):  
Nikolay N. TUPITSYN
Keyword(s):  
Attitude Control ◽  
Feasibility Studies ◽  
Propulsion System ◽  
Zero Gravity ◽  
Liquid Propellant ◽  
Propulsion Systems ◽  
Rocket Propulsion ◽  
Liquid Rocket Propulsion ◽  
Liquid Rocket ◽  
Main Engine

The paper presents results of preliminary design feasibility studies of using inertial settling of liquid propellant in tanks of space liquid rocket propulsion systems and separating from the propellant the ullage gases formed in zero gravity by means of centrifugal forces generated when the orbital unit performs the programmed turn maneuver proposed by the author. It shows that performing propellant settling and ullage gas separation by means of the separating turn maneuver makes it possible to significantly reduce propellant consumption in propulsion systems for attitude control and ullage engines. Key words: space liquid rocket propulsion system, main engine, separation of ullage gases from liquid propellant, separating turn maneuver of the orbital unit.

Features of the system approach to safety stand tests of liquid rocket propulsion systems

2020 ◽  
pp. 40-50
Author(s):  
В.А. Бершадский
Keyword(s):  
Basic Concept ◽  
System Approach ◽  
Functional Model ◽  
Industrial Safety ◽  
Propulsion Systems ◽  
Rocket Propulsion ◽  
Effective Application ◽  
Liquid Rocket Propulsion ◽  
Liquid Rocket

Пояснена необходимость разработки и реализации специальных мероприятий при применении системного подхода к безопасности стендовых испытаний двигательных установок ракет. Определена основная концепция промышленной безопасности при стендовых испытаниях кислородно-водородных двигательных установок. Изложено и обосновано содержание специальных мероприятий по безопасности испытаний. Предложена функциональная модель безаварийного проведения испытаний и определены мероприятия для её эффективного применения. It explains the need to develop and implement special measures for a systematic aproach to the safety of stand tests of rocket propulsion systems. The basic concept of industrial safety during stand tests of oxygen-hydrogen propulsion systems is defined. The content of special measures for test safety is described and justified. A functional model of trouble-free testing is proposed and measures for effective application are defined.

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