Propulsion System for Panel ExTension SATellite (PETSAT)

Paper number

IAC-05-C4.1.09

Author

Dr. Hironori Sahara, University of Tokyo, Japan

Coauthor

Prof. Shinichi Nakasuka, University of Tokyo, Japan

Coauthor

Ms. Chisato Kobayashi, Astro-Technology SOHLA, Japan

Year

2005

Abstract

Space Oriented Higashi-osaka Leading Association (SOHLA) in Japan is planning to launch SOHLA series microsatellites in the five years. A Panel ExTension SATellite (PETSAT), which was proposed by Nakasuka Laboratory in Univerisity of Tokyo, will be the second one named SOHLA-2. The PETSAT consists of multipurpose panels of 30 x 30 x 5 cm, each of which is specialized for a particular purpose, that is, missions, power supplying, CDH, ADCS, communications, and propulsion system. It shortens the development period for your compact plug-in panels with specified purposes, and for your PETSAT by combining the panels with simple plug-in connections.
Some PETSAT require propulsion system for orbit compensation, orbit transferring, or Eco-Friendly End-of-Life De-Orbiting (EFELDO), and you can obtain desirable propulsion performance on demand by selecting chemical propulsion, electric propulsion, or the others. The propulsion system will be supplied as a propulsion subsystem panel of 30 x 30 x 5 cm, for example. If you require more delta-V, you can tack on the additional propulsion subsystem panels to your PETSAT.
Now we are developing the chemical propulsion subsystem for the PETSAT, with the safer and simpler handling characteristics as a matter of first priority. We chose safer 30 percent hydrogen peroxide solution for monopropellant propulsion, or as an oxidizer for bipropellant of ethanol fuel. As the result of basic estimations, the monopropellant and bipropellant propulsion attain 100 and 200 seconds of specific impulse with 1-10 N of thrust magnitude range, respectively. An appropriate catalyst was chosen for the higher efficiency decomposition of hydrogen peroxide. We already started to develop the propulsion subsystem panel capable of 50 m/s of delta-V at reasonable cost by promoting COTS know-how cultivated in a cold gasjet propulsion system for our extendible FUROSHIKI satellite. Also, the propulsion system for PETSAT will be diverted for other microsatellites.

Abstract document

IAC-05-C4.1.09.pdf

Manuscript document

IAC-05-C4.1.09.pdf (🔒 authorized access only).

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