• Journal of the Korean Society of Propulsion Engineers
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• v.11 no.1
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• pp.18-26
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• 2007

A development of monopropellant thruster for microsatellite that uses concentrated hydrogen peroxide is described. Catalyst, the most important component in the thruster, was prepared and coated on a monolith honeycomb. Performance evaluation of thruster was peformed by considering the efficiency of characteristic velocity and ignition delay. As a result, 96.0% of $C^*$ efficiency was obtained at designed propellant flowrate and steady state operating condition.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.10
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• pp.92-98
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• 2006

An 1 lbf of NASA standard monopropellant thruster, MRE-1, is used for KOMPSAT (Korea Multi-Purpose Satellite) which is launched in 2006 and provides reliable and cost-effective means for attitude and maneuvering control system. The monopropellant thruster obtains required thrust by thermal decomposition process of propellant through catalyst bed. During firing, the decomposition plays a role of a heat source that may occur an excessive radiation heat transfer to peripheral structures and electronics in relatively low temperature condition.Therefore, the radiation heat shield is needed to prevent the critical radiative heat exchange between thruster and satellite during firing. This paper summarizes an overall development process of radiation heat shield from the design engineering up to the manufacturing.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.406-408
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• 2017

Ammonium dinitramide (ADN) Low toxicity monopropellant based 1N class thruster and test equipment were developed. Compared with the hydrazine which used in existing satellite thruster, ADN is easy to handle and has excellent physical characteristics such as density and specific impulse. Due to these characteristics, ADN is attracting attention as an eco-friendly propellant. In this paper, 1N class thruster and thrust measurement system was designed for performance testing of ADN monopropellant. The composition of the propellant for the design and experiment was set at 11.2: 25.4: 63.4 for each of Methanol: $H_2O$: ADN.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.739-745
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• 2017

Research of ADN-based monopropellant thruster is progressed by developed countries in Europe to replace toxic hydrazine, and ADN-based monopropellant thruster system is the only system that was proved in space environment. In this research, ADN-based propellant and catalyst was fabricated to develop ADN-based monopropellant thruster, and catalytic combustion performance with fabricated propellant and catalyst were evaluated with DSC-TG analysis. Catalytic combustion of propellant and catalyst was determined with firing test using 5 N scale liquid monopropellant thruster.

• 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.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.19-22
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• 2009

Design and performance evaluation of $H_2O_2$ monopropellant thrusters to be used at attitude control of space launch vehicles were presented in this paper. Flight model thrusters were designed after two reactors for 100, 250 Newton were conformed at engineering model. Each thruster was evaluated by measurement of characteristic velocity, thrust, specific impulse, and pulse response times.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.04a
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• pp.179-182
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• 2007

The new KOMPSAT in preliminary design phase will utilize 4.45 N monopropellant thrusters for attitude and orbit control. In this paper, a numerical plume analysis is performed to verify the effects of thruster plume on the satellite with a 3-D satellite base region model by DSMC. As a result, plume behaviors such as overall plume temperature, total density and thermal radiation to solar array are estimated.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.05a
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• pp.145-148
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• 2008

A 50 Newton monopropellant thruster being developed for attitude control in a variety of aerospace application systems is described in this paper. A scaled down thruster with platinum on aluminum oxide in the reaction chamber was tested to determine the catalyst capacity. A scaled up thruster, was designed and fabricated using data obtained on small scale device, was evaluated by decomposition efficiency based on temperature, efficiency of characteristic velocity, and measurement of thrust. The performance of a scaled up thruster was 42 Newton in thrust, 98 % in efficiency of characteristic velocity, and 123 sec in specific impulse at sea level.

• Journal of the Korean Society of Propulsion Engineers
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• v.12 no.3
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• pp.24-33
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• 2008

A 50 Newton monopropellant thruster being developed for attitude control in a variety of aerospace application systems is described in this paper. A scaled down thruster with platinum on aluminum oxide in the reaction chamber was tested to determine the catalyst capacity. A scaled up thruster which was designed and fabricated using data obtained from a small scale device was evaluated by its decomposition efficiency based on the temperature, the efficiency of characteristic velocity, and the measurement of thrust. The performance of a scaled up thruster was marked by a measured thrust of 42 Newton, 98 % efficiency of the characteristic velocity, a specific impulse of 123 sec at sea level.

• Journal of the Korean Society of Propulsion Engineers
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• v.14 no.1
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• pp.1-10
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• 2010

Design and performance evaluation of $H_2O_2$ monopropellant thrusters to be used at reaction control of space launch vehicles were presented in this paper. Design thrust level was determined as 100, 250 Newton which is nominal thrust level for commercial space launch vehicles. Qualification thruster models including solenoid valves were developed after the reactor design were evaluated at engineering thruster models. Each thruster was evaluated by measurement of characteristic velocity, thrust, specific impulse, and pulse response times at sea level test condition.