• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.04a
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• pp.102-105
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• 2007

The performance evaluation of the micro thruster utilizing hydrogen peroxide decomposition is described. The catalyst bed was made of porous ceramic material($Isolite^{(R)}$) with large surface to mass ratio. 14%wt platinum was loaded on the catalyst support as a catalyst. Hydrogen peroxide with 85% concentration was used as a monopropellant. The length of the catalyst bed and the feed pressure of the hydrogen peroxide were taken as the parameters for the experiment. All experiments were carried out under cold start condition for 30 seconds. The $c^*$ efficiency was evaluated for each test case using measured pressure data. For the catalyst support length of 30 mm and feed pressure at 5.51 bar, satisfactory $c^*$ efficiency beyond 95% was observed.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.375-379
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• 2008

In this paper, a 10N class liquid propellant rocket utilizing a dissolving reaction of hydrogen peroxide is constructed and tested. Through a series of designs, seven orifices with a diameter of 200 ${\mu}m$ and a nozzle with a neck of 2.5mm in diameter and area ratio of 2.56 were made. The platinum coated on Isolite was used for catalyst. 90wt% peroxide pressed at 20 bar by nitrogen gas was used for performance evaluation. The length of the catalyst bed and the load of platinum was taken as the parameters for this experiment. For the catalyst support length of 4cm loaded on 5wt% platinum, satisfactory $c^*$ efficiency and stable thrust was observed. The light weight body of the rocket was composed of aluminum. Rocket rose about 10m with relatively constant velocity in launching test.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.05a
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• pp.111-114
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• 2008

The performance evaluation of a micro monopropellant thruster is described in this paper. The platinum which has stable physical and chemical properties is used as a catalyst. The ceramic form, named Isolite is chosen as a catalyst bed. Hydrogen peroxide whose concentration is up to 90wt% is supplied into thruster by direct pressurization with nitrogen gas. The $c^*$ efficient is calculated to evaluate the performance of a thruster. The pressure rise time, pressure decent time and reaction delay are synthetically considered.