Abstract
A Ф0.8mm micro-solid propellant rocket array thruster for simple attitude control of a 10 kg class micro-spacecraft was tested in vacuum. The micro-thruster uses boron/potassium nitrate propellant (NAB), because NAB has ignition temperature as low as 500°C, and easily start to burn in vacuum. For a half of the rockets, an ignition aid (RK) was also loaded. Ignition was succeeded in vacuum with NAB + RK and NAB. The maximum impulse thrust of 4.6ˣ10-4 Ns, which is approximately a half of our requirement, was obtained with NAB. Compared to NAB, NAB + RK generated lower impulse thrust. The success rate of ignition was as low as 30%, although RK was used. These results suggest that RK has no benefit for the ignition of NAB, and other kinds of ignition aid should be found.
Original language | English |
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Pages (from-to) | 222-227 |
Number of pages | 6 |
Journal | IEICE Electronics Express |
Volume | 1 |
Issue number | 8 |
DOIs | |
Publication status | Published - 2004 |
Keywords
- MEMS
- ignition aid
- impulse thrust
- micro-propulsion
- micro-thruster
- solid propellant
ASJC Scopus subject areas
- Electronic, Optical and Magnetic Materials
- Condensed Matter Physics
- Electrical and Electronic Engineering