A Preliminary Study on Hydrazine Decomposition by Discharge Plasma

Paper number

IAC-05-C4.P.07

Author

Mr. Junichiro Aoyagi, Tokyo Institute of Technology, Japan

Coauthor

Dr. Akira Kakami, Kyushu Institute of Technology, Japan

Coauthor

Prof. Haruki Takegahara, Tokyo Institute of Technology, Japan

Coauthor

Prof. Takeshi Tachibana, Kyushu Institute of Technology, Japan

Coauthor

Mr. Hiroyuki Mishima, Mitsubishi Heavy Industries, Ltd., Japan

Coauthor

Mr. Katsumi Furukawa, Mitsubishi Heavy Industries, Ltd., Japan

Coauthor

Mr. Noriyoshi Saitoh, Japan Aerospace Exploration Agency (JAXA), Japan

Coauthor

Dr. Ryuichi Nagashima, Japan Aerospace Exploration Agency (JAXA)/ISAS, Japan

Coauthor

Dr. Kyoichi Kuriki, Tokyo Institute of Technology, Japan

Year

2005

Abstract

Hydrazine Catalyst Thruster is applied to many spacecraft propulsion systems.  Frequently, the lifetime and reliability of the thruster are restricted by the degradation of catalyst.  For example, particulates of catalyst cause failure of thruster by jamming injector orifices.  Also such characteristics make the grand validation test difficult.

In this study, we propose the utilization of the low power discharge plasma to assist decomposition of hydrazine in order to overcome the problems concerned with catalyst.  It has been known that the activity of discharge plasma is high enough to induce various chemical reactions, but poor capability of electrical power subsystem of satellite prevented it from applying to propulsion system. With recent growing of the use of electric propulsion, electrical components are improved enough to realize this new plasma-utilized thruster.

To demonstrate that discharge plasma initiates and sustains decomposition of hydrazine, we conducted a preliminary experiment with a bucket type reaction chamber.  As a discharge plasma source, pulse or stationary AC discharge was employed.  When the plasma was generated in the chamber filled with gaseous hydrazine, the temperature and the pressure were increased immediately.  These results indicate that it is worthwhile applying the discharge plasma to the hydrazine thruster system.  The detailed result of this test will be also reported in this paper.

Abstract document

IAC-05-C4.P.07.pdf

Manuscript document

IAC-05-C4.P.07.pdf (🔒 authorized access only).

To get the manuscript, please contact IAF Secretariat.