Microfluidics of Liquid Propellant Microthruster for Pico-Satellites

Yasuhiko Osaki, Koji Takahashi

Research output: Contribution to journalArticle

3 Citations (Scopus)

Abstract

This paper treats a liquid propellant microthruster because its thrust flexibility and small tank are advantageous to pico-satellites for many types of missions. Two major fluidic concerns are investigated using test devices fabricated by MEMS technique. One is the catalytic decomposition of hydrogen peroxide in a microchannel. The other is the effect of wettability on two-phase flow. A platinum-coated channel with a height of 5 μm was found to work well because of its large surface-volume ratio. However, the heat dissipation into the structure components is critical especially for the starting period. An additional electric heater was tested and discussed for quick and effective operation. The dependence of boiling flow on surface wettability should be concerned for the fluidic design of microchannel-based liquid microthrusters. The test results showed that the electric heater is effective to obtain practical thrust from liquid propellant.

Original languageEnglish
Pages (from-to)436-441
Number of pages6
JournalIEEJ Transactions on Sensors and Micromachines
Volume123
Issue number10
DOIs
Publication statusPublished - Jan 1 2003

Fingerprint

Liquid propellants
Fluidics
Microchannels
Microfluidics
Wetting
Satellites
Heat losses
Hydrogen peroxide
Two phase flow
Boiling liquids
MEMS
Platinum
Decomposition
Liquids

All Science Journal Classification (ASJC) codes

  • Mechanical Engineering
  • Electrical and Electronic Engineering

Cite this

Microfluidics of Liquid Propellant Microthruster for Pico-Satellites. / Osaki, Yasuhiko; Takahashi, Koji.

In: IEEJ Transactions on Sensors and Micromachines, Vol. 123, No. 10, 01.01.2003, p. 436-441.

Research output: Contribution to journalArticle

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