development of close-loop pressurization system using CO2

Paper number

IAC-14,D2,5,5,x24643

Author

Mr. Jun Matsumoto, The University of TOKYO, Graduate school, Japan

Coauthor

Dr. Junichiro Kawaguchi, Japan Aerospace Exploration Agency (JAXA), Japan

Coauthor

Mr. Shunichi Okaya, Japan Aerospace Exploration Agency (JAXA), Japan

Coauthor

Mr. Hiroshi Igoh, Japan Aerospace Exploration Agency (JAXA), Japan

Coauthor

Dr. Shigeyasu Iihara, IHI Aerospace Co, Ltd., Japan

Coauthor

Mr. Naohiro Suzuki, Japan Aerospace Exploration Agency (JAXA), Japan

Coauthor

Mr. Seiichi Yasuda, Japan Aerospace Exploration Agency (JAXA), Japan

Coauthor

Mr. Daisuke Yasuda, Japan Aerospace Exploration Agency (JAXA), Japan

Year

2014

Abstract

In a conventional liquid engine system, a gas pressurization system or a turbo pump pressurization system is applied to pressure oxidant and fuel. In these system, it is required to equip a large tank to store the pressurization gas or a heavy turbo pump. In flight systems which requires weight saving, this heavy pressurization system is a restriction to design whole engine systems.

  In order to break this situation, a new pressurization system using CO$_2$ has been developed by Japan Aerospace Exploration Agency (JAXA). This system is a kind of gas pressurization system. The pressurization source CO$_2$ is, however, stored in liquid phase. Compared to conventional pressurization systems, it can reduce a weight of a tank storing the pressurization source because the volume of the liquid source is small. During burning of the engine, LCO$_2$ is vaporized by regenerative cooling strategy and GCO$_2$ pressures oxidant and fuel. In order to control the pressure of CO$_2$, this system has a instrument called charger. It is a kind of piston and it pressures CO$_2$. There is a close-loop line in this system and the piston is driven by CO$_2$ itself. From a perspective of energy, kinematic energy to drive the piston is supplied through the regenerative cooling.  

  This paper shows a mathematical modeling of this close-loop pressurization system and a result of a demonstration experiment conducted in Akiruno, Japan.  In order to drive this close-loop system stably, several tuning of parameters was required. By this demonstration experiment, a feasibility of this new pressurization system is shown. In future, this system is applied to a N$_2$O/Ethanol liquid rocket engine which is now under development in JAXA.

Abstract document

IAC-14,D2,5,5,x24643.brief.pdf

Manuscript document

IAC-14,D2,5,5,x24643.pdf (🔒 authorized access only).

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