• 한국항공우주학회지
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• 제35권12호
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• pp.1115-1120
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• 2007

본 논문은 기둥 구조의 전극이 내부에 존재하는 노즐을 이용한 정전 분무 마이크로 추진 장치의 새로운 메커니즘을 제시하였다. 기둥 구조의 노즐로 인한 제팅의 효율 증진을 수치적 및 실험적으로 연구하였다. 노즐 상부에 존재하는 전극에 인가된 전압으로 인하여 액면에 형성된 전기장은 액체의 분무를 가능하게 하며 기둥 구조의 전극은 액면의 중앙 부분에 전기장이 집중되도록 하여 제팅을 효율적으로 할 수 있게 하였다. 또한 노즐 크기에 따른 필요한 인가전압의 차이에 대한 연구를 수행하였으며 본 연구로부터 수 마이크로미터의 노즐에 대해서 500V 이하의 전압에서 구동이 가능함을 보였다.

• 한국추진공학회지
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• 제17권6호
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• pp.30-37
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• 2013

우주비행체의 주 엔진 및 자세제어용 추력기로 적용 가능한 단일액체추진제 하이드라진 추력기의 촉매대 최적설계형상 도출을 위한 지상연소시험을 수행하였다. 추력, 비추력, 연소실 압력, 특성속도, 그리고 하이드라진 분해반응률 등을 추력실 길이변화에 따라 고찰하고, 추진제 공급압력과 성능변수가 갖는 상관관계를 제시한다. 성능평가결과, 시험조건 내에서의 촉매대 길이증가는 추력기의 성능저하를 야기하고, 공급압력 변이에 따른 추진제 소모 효율성 또한 떨어뜨리는 것이 확인되었다.

• 한국전산유체공학회지
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• 제21권2호
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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.

• 대한조선학회논문집
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• 제55권3호
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• pp.196-204
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• 2018

Present paper shows the basic design procedure for platform support vessel operating in open sea, and hull form development process. General design concept considering the operating mission, operating sea condition and shipping freight, etc. is explained shortly. For the hull form design, the initial hull form was designed based on the reference PSVs. The resistance and propulsion test results for the initial hull form with twin Azimuth thruster were analyzed and a few items for improvement were derived. At the next stage, main parameters including Length, Cp-curve, Cb, Lcb, etc. were changed totally for the hull form improvement. Furthermore, 3 different bulbous bows for the fore-body design to reduce the wave resistance and after-body design to reduce the residual resistance were carried out. The best hull form among the 3 fore-bodies with same after-body was selected through the comparison of wave resistance calculation results. Twin ducted Azimuth thruster with the smaller propeller diameter than the former were adapted to increase the propulsive efficiency. The final hull form with the twin Azimuth thruster was evaluated to satisfy more than the target design speed 14 knots in sea condition with sea margin 15% at the 5,000kW BHP through the model test in KRISO.

• 한국추진공학회지
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• 제25권5호
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• pp.65-72
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• 2021

소형위성의 궤도조정 및 궤도유지에 활용될 수 있는 700 W급 홀추력기 랩모델을 개발하였다. 스케일링 방정식을 사용하여 방전채널의 크기를 선정하였으며, 자기장이 방전채널 중심선을 기준으로 대칭성을 가지면서 방전채널 바깥에서 최대가 되도록 설계하였다. 개발된 홀추력기의 방전시험은 2.0×10^-5 Torr 이하의 배경압력을 갖는 진공 환경에서 수행되었으며 추력 스탠드를 이용하여 추력을 측정하였다. 양극전압을 300 V로 고정하고 양극유량과 코일전류를 변수로 하여 추력을 측정하였으며, 양극유량 2.36 mg/s, 코일전류 2.4 A 조건에서 양극전력 620 W에서 추력 38 mN, 통합비추력 1,540 s, 양극효율 50 %로 가장 높은 성능을 보였다.

• 에너지공학
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• 제2권1호
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• pp.38-44
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• 1993

Electromagnetic seawater thrusters may be classified into four general categories : internal duct dc, external field dc, internal peristaltic ac, and external peristaltic ac. Internal duct dc thrusters offer the advantages of low magnetic field leakage, simple construction, and potentially high reliability. The most efficient internal duct configuration consists of converging inlet nozzle and a straight discharge duct. Ideal efficiency calculations based on the one-dimensional Bernoulli equation show that thrusters should be designed with large cross-sectional areas and operate at low discharge velocities. In practice, this may be accomplished by using multiple thruster ducts. Conductivity enhancement, high magnetic fields, and long electrodes will also improve efficiency.

• International Journal of Aeronautical and Space Sciences
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• 제18권3호
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• pp.512-521
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• 2017

This paper reports development process of a university-based sounding rocket using simplified hybrid rocket propulsion system for low-altitude flight application. A hybrid propulsion system was tried to be designed with as few components as possible for more economical, simpler and safer propulsion system, which is essential for the small scale sounding rocket operation as a CanSat carrier. Using blow-down feeding system and catalytic ignition as combustion starter, 250 N class hybrid rocket system was composed of three components: a composite tank, valves, and a thruster. With a composite tank filled with both hydrogen peroxide($H_2O_2$) as an oxidizer and nitrogen gas($N_2$) as a pressurant, the feeding pressure was operated in blowdown mode during thruster operation. The $MnO_2/Al_2O_3$ catalyst was fabricated for propellant decomposition, and ground test of propulsion system showed the almost theoretical temperature of decomposed $H_2O_2$ at the catalyst reactor, indicating sufficient catalyst efficiency for propellant decomposition. Auto-ignition of the high density polyethylene(HDPE) fuel grain successfully occurred by the decomposed $H_2O_2$ product without additional installation of any ignition devices. Performance test result was well matched with numerical internal ballistics conducted prior to the experimental propulsion system ground test. A sounding rocket using the developed hybrid rocket was designed, fabricated, flight simulated and launch tested. Six degree-of-freedom trajectory estimation code was developed and the comparison result between expected and experimental trajectory validated the accuracy of the developed trajectory estimation code. The fabricated sounding rocket was successfully launched showing the effectiveness of the simplified hybrid rocket propulsion system.

• 한국항공우주학회지
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• 제41권4호
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• pp.299-304
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• 2013

이온성 액체 추진제인 HAN은 무독성의 높은 저장성을 갖는 단일 추진제로서 메탄올을 혼합하여 비추력을 향상시켜 하이드라진을 대체할 수 있을 있다. HAN은 하이드록실아민과 질산의 산-염기 반응을 통해 합성하며, 메탄올과 8.2:1의 비율로 혼합한다. HAN의 분해를 위해서 이리듐 촉매를 사용하며, 하나의 오리피스를 갖는 1 N급 추력기를 사용하여 HAN/메탄올 추진제의 성능 평가를 수행하였다. 메탄올 연소로 인해 반응 생성물의 온도가 높기 때문에 디스트리뷰터의 열적 안정성을 향상시키기 위해 세라믹 재료를 적용하였다. 완전한 분해를 위해서는 최소 $400^{\circ}C$의 예열 온도를 필요로 하였다. 높은 $C^*$ 효율을 얻기 위해서는 가압 압력이 높아져야 했으며, 이로 인해 촉매 상단의 분해 성능이 저하되면서 전체 추력기 성능 저하가 유발되었다. 이를 해결하기 위해 미세한 금속 메쉬를 인젝터 후단에 삽입하여 추진제의 분무 특성을 향상시켰으며, 실험 결과 촉매의 성능 저하 현상이 개선되었음을 확인하였다.

• 로봇학회논문지
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• 제13권2호
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• pp.103-112
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• 2018

In this paper, a high performance underwater vehicle which can be manufactured at low cost is designed and fabricated, and its performance is verified through experiments. To improve efficiency, the Myring equation is used to design the appearance and the duct structure including the thruster is planned to increase the propulsion efficiency while reducing the drag force. Through various methods, it is secured stable waterproof performance, and also is devised to have high speed movement and turning performance. The developed underwater vehicle is equipped with a high output BLDC motor to achieve a linear speed of up to 2 m/s and can change direction rapidly with stability through four rudders. The rudders are driven by coupling a timing belt and a pulley by extending the axis of a servo motor, and are equipped at the end of the body to turn heading. In addition, for stable posture control, the roll keeps its internal center of gravity low and maintains its stability due to restoring force. By controlling the four rudders, pitch and yaw are handled by the PID controller and show stable performance. To investigate the horizontal turning performance, it is confirmed that the yaw rate controller is designed and stable yaw rate control is performed.

• 한국해양공학회지
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• 제26권6호
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• pp.39-45
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• 2012

Underwater robots are generally used for the construction of seabed structures, deep-sea ecosystem research, ocean energy development, etc. A ducted marine propulsor is widely used for the thruster of an underwater robot because of its collision protection, efficiency increase, cavitation reduction, etc. However, the flow of a ducted propeller is very complex because it involves strong flow interactions between the blade impeller and duct. The present work aimed to design a ducted propeller using 2-D strip theory and CFD analysis. The hydrodynamic forces (i.e. and ) were computed to set the local angle of attack in a spanwise direction of the propeller blade. After the propeller design, performance coefficients such as the thrust, torque, and efficiency were computed to check whether the designed performance was achieved. To validate the present analysis, the thrust was compared with experimental data and good agreement was obtained.