• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.5
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• pp.490-495
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• 2009

A small Hall-effect thruster with a thrust range near 10 mN and a specific impulse of about 1500 s has been designed to control or maintain the orbits of small satellites. The thruster system consists of a hall-effect thruster head, a power processing unit and a Xenon (Xe) gas feed system. The total mass, the consumed electric power and the efficiency of the thruster are approximately 10 kg, 300W and 30%, respectively. Analyses results that support the selection of the thruster for small satellites are provided along with a brief description of the thruster system.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.03a
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• pp.550-552
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• 2008

A small hall thruster with a thrust of about 10 mN and a specific impulse of about 1500 s is being developed with an intent to control or maintain the orbits of small satellites. The total mass, consumed electric power and efficiency of the thruster are approximately 10 kg, 300W and 30%, respectively. The thruster system consists of a hall thruster with a cylindrical cross section, a power processing unit and a Xenon(Xe) gas feed system. Laboratory examination of the thruster performance finds that the thruster meets the design specification.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.753-756
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• 2017

With the advancement of technology, miniaturization, integration, and weight reduction have become possible, and the existing medium and large satellites have been replaced by small satellites, and the need for a micro thruster has emerged. Laser ablation micro-thruster is a new type thruster using laser ablation. It is emerging as a new candidate in micro-thrusters with wide thrust range and low single impulse thrust. The objective of present study is to introduces the structure, propellant, and research trends of the laser ablation micro-thruster.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.5
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• pp.496-501
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• 2009

The thruster head unit of a 300 W cylindrical Hall thruster was developed for the propulsion system of small satellites. The magnetic topology in the thruster channel is a key parameter to achieve high performances. Two types of magnetic circuit structures were designed and manufactured to compare the thrust levels and efficiencies. Also the endurance test was conducted to measure the stable operation duration of the thruster head and to find degree of erosion after extended operation.

• Journal of the Korean Society of Propulsion Engineers
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• v.22 no.1
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• pp.98-106
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• 2018

With the advancement in technology, miniaturization, integration, and weight reduction of satellite components have become possible. In this regard, existing medium and large satellites have been replaced by small satellites. As the demand for small satellites increases, the need for micro-thrusters has emerged for precise attitude and position control. A laser ablation micro-thruster, which generates thrust by using ablation jets that offer a wide range of thrusts and low-impulse thrusts, is considered as an alternative for micro-thrusters in small satellites. The objective of the present study is to introduce configurations of the laser ablation micro-thruster and its research trend.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.05a
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• pp.66-69
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• 2006

A two-dimensional Particle-In-Cell (PIC) simulation of a Hall thruster is presented. The thruster is being developed for orbit transfer and correction of a small satellite. Preliminary investigation of the simulation result finds well separated acceleration and ionization layers. The simulation further shows that collisional ionization of the xenon neutrals allows sufficient acceleration of the ionized plasmas that is adequate for the intended correction and transfer of small satellite orbits. Anticipated performance of the thruster based upon the present results will be calculated.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2003.05a
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• pp.147-150
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• 2003

The purpose of this research was to develope components of micro solid propellant thruster. Micro solid propellant thruster had four basic components: combustion chamber, nozzle, solid propellant and micro heater for ignition. A performance of micro heater and characteristic of solid propellant was investigated. Micro heater was fabricated by conventional MEMS process and Platinum layer was used for heating element. Effect of geometry parameters on micro heater was tested. The temperature responses of heater with respect to each parameters was compared for a given electrical power. The characteristic of solid propellant(HTPB/AP) was investigated to obtain burning velocity in small chamber. Additionally, a capacity of filling propellant with high viscosity in small chamber was checked to guarantee for the micro fabrication.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.645-648
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• 2011

Hydrazine which has been used as monopropellant shows high performance, but because of its high toxicity research for new green propellant that could replace hydrazine is going on. Ionic liquid propellant that is one of the green propellant has lower toxicity, higher specific impulse, and higher density than hydrazine. To design the thruster which use Hydroxylamine Nitrate (HAN), one of ionic liquid propellant, as a propellant, a quantity of catalyst for full decomposition of a propellant is needed. In this study, reference point for HAN thruster design could be suggested through a design of a small scale thruster which used HAN propellant, and propellant decomposition capability evaluation with characteristic velocity efficiency.

• Journal of Power System Engineering
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• v.13 no.5
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• pp.18-24
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• 2009

This paper shows the result of development about the revolution system of azimuth thruster which of power is less than 250kW for small ship. Advanced Azimuth revolution system can revolve propeller and rudder from 360 degree so that this system for vessel maneuvering can be excellent of propulsion effectively. Fluid power control system for azimuth thruster is designed with PID control system by using CEMTool/SIMTool program. And the actuator used for servo valve can control rudder angle, pressure and direction. The first, We had a test for the angle control of revolution system. The result of angle control confirmed that it has the good efficiency from experiment result of time input degree $30^{\circ}$, $90^{\circ}$ and $180^{\circ}$. The second, We had to a test for the pressure characteristic of hydraulic motor. As a result, We confirmed the maximum pressure 3.5MPa and steady state 0.7MPa nom experiment result of time input degree $30^{\circ}$. In this paper, it is identified the pressure characteristic of hydraulic motor and angle control for azimuth thruster by AMESim, and it has been confirmed the usefulness of AMEsim modeling was verified by comparison between AMESim simulation results and experiments results.

• 한국전산유체공학회:학술대회논문집
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• 2009.04a
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• pp.130-134
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• 2009

CFD analysis of the fuel injection pattern and the flow field surrounding the liquid propellant injector of a small thruster is performed. A good agreement is shown with PIV test data for the initial configuration. Analysis on various injector shapes is performed to observe the effect of injector shape on the trajectories of liquid droplet. A various shapes of injector is investigated to enhance spray pattern of the small injector.