Micro Bi-Propellant Thruster
The Monopropellant Thruster developed by AIT is a low thrust (less than 1N) propulsion solution. Usage of hydrogen peroxide not only results in a high impulse density but offers also significantly reduced development and operational costs. Especially due to the latter, such a system could replace the present hydrazine propulsion solution. And the smallest 1-2 N bipropellant thruster based operating with green propellant.
Furthermore the usage of green propellants (non-toxic and non-carcinogenic) will significantly reduce the operational costs. Envisioned application for this system includes attitude control and accurate positioning of medium and small satellites. A parallel development of the bipropellant technology for ignition purposes is under investigation.
Characteristics and performance data are summarized in the following table:
AIT Micro Bi-Propellant Thruster
| Thrust | 1.7 -1.9 N |
| Specific Impulse (vacuum) | 290 – 330 s |
| Thruster mass | less than 100 g |
| Fuel | Ethanol, Kerosene, … |
| Oxidizer | Hydrogen Peroxide (87.5%) |
| Power | less than 3 W (valves) |
The present development level is roughly equivalent to TRL 3. Further developments are ongoing.
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left: AIT Bipropellant showing details of the injector and cooling system
right: Bipropellant thruster assembled in the test facility
Abb.: AIT system study of an ignition system for large scale chemical propulsion systems
carsten.scharlemann@ait.ac.at