• Bulletin of the Korean Space Science Society
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• 2007.10a
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• pp.139-143
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• 2007

Electric propulsion has become a cost effective and sound engineering solution for many space applications. The success of SMART-1 and MUSES-C developed by European Space Agency (ESA) and Japan Aerospace Exploration Agency (JAXA) each proved that even small spacecraft could accomplish planetary mission with electric propulsion systems. A small electric propulsion system which is Hall effect thruster like SMART-1 is under development by SaTReC and GDPL (Glow Discharge Plasma Lab.) in KAIST for the next microsatellite, STSAT-3. To achieve optimized propulsion system, it is very necessary to understand plasma motions of Hall effect thruster. In this paper, we try to approach comprehensive plasma model with the particle simulation complementary to Particle In Cell (PIC) simulation. We think these two different approaches will help experimenters to optimize Hall effect thruster performances.

• Journal of computational fluids engineering
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• v.21 no.2
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• pp.112-119
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• 2016

NEXTSat-1 is the next-generation small-size artificial satellite system planed by the Satellite Technology Research Center(SatTReC) in Korea Advanced Institute of Science and Technology(KAIST). For the control of attitude and transition of the orbit, the system has adopted a RHM(Resisto-jet Head Module), which has a very simple geometry with a reasonable efficiency. An axisymmetric model is devised with two coil-resistance heaters using xenon(Xe) gas, and the minimum required specific impulse is 60 seconds under the thrust more than 30 milli-Newton. To design the module, seven basic parameters should be decided: the nozzle shape, the power distribution of heater, the pressure drop of filter, the diameter of nozzle throat, the slant length and the angle of nozzle, and the size of reservoir, etc. After quasi one-dimensional analysis, a theoretical value of specific impulse is calculated, and the optima of parameters are found out from the baseline with a series of multi-physical numerical simulations based on the compressible Navier-Stokes equations for gas and the heat conduction energy equation for solid. A commercial code, COMSOL Multiphysics is used for the computation with a FEM (finite element method) based numerical scheme. The final values of design parameters indicate 5.8% better performance than those of baseline design after the verification with all the tuned parameters. The present method should be effective to reduce the time cost of trial and error in the development of RHM, the thruster of NEXTSat-1.

• Bulletin of the Korean Space Science Society
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• 2007.04a
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• pp.59-59
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• 2007

• Proceedings of the KIEE Conference
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• 2008.07a
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• pp.643-644
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• 2008

This paper is analyzed the effect on characteristics of thrust force of linear induction motor(LIM) by rotational type tester. Many kinds of tester have a rotational shape because of a finite length of railroad. Whereas effects by using rotational type tester are generally unknown. For reason of that, this paper will be analyzed the effect on characteristics by rotational type tester using 2D finite element method(FEM), and then will be compared a thrust force between linear type tester and rotational type tester.

• Journal of Aerospace System Engineering
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• v.15 no.1
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• pp.32-39
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• 2021

Electric propulsion aircraft are being actively researched in the aviation field in recent years to solve environmental and noise problems caused by existing gas turbine engine. In particular, research on a thrust motor as a core component of an electric power propulsion system and an inverter for driving it is actively being conducted. In this paper, a motor with high specific power is selected to determine characteristics of aircraft that are sensitive to weight and volume. Power loss of the inverter is then simulated. In the simulation, the selected motor and power device were modeled using PSIM, a power electronics analysis tool. Inverter power loss according to switching frequency was then analyzed.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.50 no.1
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• pp.1-12
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• 2022

Wind tunnel test for a small scale electric ducted fan with a 104mm diameter was conducted to analyze the aerodynamic characteristics when it was used as a propulsion system of tilt-propeller UAV. Experimental conditions were derived from flight conditions of a sub-scaled OPPAV. Forces and moments of the ducted fan model were measured by a 6-axis balance and 3-dimensional wake vectors which could induce an aerodynamic influence in the vehicle were measured by 5-hole probes. Thrust and torque on hover and cruise conditions were measured and analyzed to drive out the operating conditions when it was applied in the sub-scaled OPPAV. On transition conditions, thrust keep its value with tilt angle variation below 40° and increase after that. But, sideforce increase constantly until 75°. The maximum axial velocity in the wake on hover and cruise conditions was around 60m/s and tangential velocity was around 12m/s. The position of the maximum axial velocity and vortex center move off the fan rotation center line as the tilt angle increases.

• Proceedings of the KIEE Conference
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• 2008.04c
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• pp.140-142
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• 2008

Thrust ripples in Permanent Magnet Linear Motor(PMLSM) are mainly generated by cogging force. Cogging force caused by the interaction between the iron core and the Permanent Magnet(PM), and end effect. This paper has proposed a control method for thrust ripples suppression and design of one-chip proceeding digital controller using TMS320LF2407. This control method is realized by Field Oriented Control(FOC) adding to current compensation. The effectiveness of proposed control method is verified by experimentation comparing between the compensation and non-compensation.

• Proceedings of the KIEE Conference
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• 1997.07f
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• pp.2146-2148
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• 1997

We had developed a prototype Linear Pulse Motor(LPM) for the linear motion actuator. In this paper, it is mentioned a new dynamic equations which is considered the nonlinearity of the thrust force of LPM. And a measuring method of ripples in the thrust forces is proposed and the ripples were measured in the laboratory. In the experimental results, it is shown the validity of the proposed measuring method for catching of the ripple values and waveforms in the thrust force.

• Proceedings of the KIEE Conference
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• 2003.10b
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• pp.30-32
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• 2003

본 논문은 LCD 제조 공정 라인에서 LCD용 원판을 다른 여러 공정으로 이송하는데 사용하기 위한 수평형 스토크 시스템의 설계 및 제작에 관한 연구이다. 구동원으로 제작된 영구 자석 여자 횡자속형 전동기는 높은 공극 자속 밀도를 얻을 수 있는 구조로 일반 선형 유도 전동기나 선형 등기기에 비해 단위 체적당 높은 출력 밀도를 얻을 수 있는 장점을 가지고 있다. 3차원 등가 자기 회로망법을 사용하여 기자력 변화에 따른 추력 및 흡인력과 같은 특성을 해석하였으며 정특성 실험을 통하여 설계 및 해석의 타당성을 검토하였다.

• Proceedings of the KIEE Conference
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• 2007.10c
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• pp.110-111
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• 2007

두개의 유니모프 진동자를 이용한 새로운 형상의 마이크로 초음파 리니어 모터를 제안하였다. 유니모프 진동자는 금속판에 판상의 압전소자가 접착되어 있으며, 두개의 유니모프 진동자가 삼각형상의 진동 커플러에 의해 연결되어 스테이터를 구성한다. 스테이터는 두 가지 진동모드(대칭모드와 비 대칭모드)를 가지고 있으며, 이 두 진동모드가 축퇴되도록 설계하였다. 스테이터의 대칭모드와 비 대칭모드를 위상차 $90^{\circ}$로 여진시킴으로써 이동체의 직선(또는 회전) 운동을 발생시킬 수 있다. 시작기 모터는 놀이 0.9 mm, 폭 1 mm, 길이 7.5 mm이며, 구동전압 $100V_{op}$, 구동주파수 300 kHz로 구동되어, 모터 최대속도 0.3 m/s, 최대 추력 6 mN을 달성하였다.