• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.1
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• pp.113-119
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• 2003

During the mission operation time, it is very important to estimate the spacecraft propellant remaining as accurately as possible. This is because the quantity of propellant is related directly to how long the satellite can be operated ín orbit. There are two different methods for spacecraft propellant gauging; the PVT method and the book-keeping method. This paper describes the characteristics and applications of these methods using the flight operation data of KOMPSAT-1. Additionally, propellant consumption rates in delta-V maneuvering and each attitude control submode are analyzed according to spacecraft operation modes. The earth search submode shows the highest propellant consumption rate.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2005.11a
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• pp.191-195
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• 2005

Propellant remains as outage at engine shutdown contributes no useful impulse to the rocket and produces an unwanted increase in burnout weight. Minimization of outage, is therfore is a basic consideration in attaining the maximum performance capability of my bipropellant liquid rocket. This paper present the calculation procedures of outage and optimum loading propellant mass. And some control methods and measurement techniques for outage are presented.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1995.11a
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• pp.49-55
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• 1995

이원 액체추진제를 사용하는 인공위성용 로켓 추진기관의 개발을 위한 핵심부품별 개념 및 상세설계, 성능해석, 성능실험용 시작품의 제작, 수류 성능실험 및 지상 연소시험이 수행되었다. 인공위성 궤도조종용 로켓 추진기관은 1.38MPa의 연소실 압력으로 4초동안 1780N(400$Ib_f$)의 평균추력을 내도록 설계되었으며, 산화제로는 질산, 연료로는 트리 에틸렌 아민(triethylene amine, TEA)과 자이리딘(xylidine)의 혼합물로 구성된 접촉발화형 이원 액체추진제를 사용하고, 추진제를 가압방식에 의해 연소실에 분사하는 방법으로 분사충돌, 미립화, 그리고 기화 후 연소시키게 된다. 효율적인 설계를 위하여 설계전용 소프트웨어를 개발하였으며, 추진기관의 핵심부품별로 유동 시뮬레이션을 수행하고, 해석결과와 수류 실험결과를 바탕으로 설계를 수정, 보완하였다. 지상 연소시험 및 수류 성능실험을 위하여 추진제 공급장치 및 계측 시스템이 설계, 제작되었고, 시스템의 작동 및 자료처리를 위한 소프트웨어를 개발하여 수류 성능실험 및 지상 연소시험에 사용하였으며, 연소시험결과 지상 평균추력 378$Ib_f$를 발생하였다.

• Journal of the Korean Society of Propulsion Engineers
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• v.18 no.5
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• pp.62-69
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• 2014

Infrared signature of rocket plume plays an important role for detection, recognition, tracking and minimzing for low observability. Infrared signatures of rocket plume with reduced smoke propellant and smokeless propellant are measured. In order to estimate the infrared signature of rocket plume, CFD analysis for flow structure of plume is performed, and layered integration method for estimating of infrared signature is used. Numerical and experimental results were in good agreement. Both propellants had similar infrared signature. Strong peak at $4.3{\mu}m$ region in the experimental results is appeared due to experimental error arising from the calibration procedure.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.11a
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• pp.146-149
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• 2006

Spray characteristics of an injector employed in mono-propellant hydrazine thrusters were investigated by PIV(particle image velocimetry) and LDA/PDA(laser/phase Doppler anemometry) techniques. The instanteneous plane image data captured by PIV measurement were examined in order to judge a pass-fail criteria of spray injection performance according to the specific pressure supplied. LDA/PDA technique were also applied to measure the velocity and droplet size of spray were not obtained from PIV measurement. The objective of this experimental study was the clear understanding of spray characteristics as well as the derivation of injector performance to understand clearly the spray characteristics by comparing the both results.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.05a
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• pp.118-122
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• 2006

For the development of a gas generator of a liquid rocket engine, the prediction of thermodynamic properties of combustion gas with respect to a propellant mixture ratio becomes critical. The present study focuses on the temperature measurement of exit combustion gas as a function of a mixture ratio through combustion tests of a fuel-rich gas generator propelled by Lox/Jet A-1. The measurement of combustion dynamic and static pressures allowed indirect estimation of thermodynamic properties like specific heat ratio, gas constant, and constant pressure specific heat. Comparing the results with empirical prediction through an interpolation reveals that the interpolation method calibrated using temperature results can be utilized as an effective tool for the design of a fuel-rich gas generator.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.10
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• pp.56-60
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• 2006

It is essential to predict thermodynamic properties of combustion gas with respect to a propellant mixture ratio for the development of a gas generator for a liquid rocket engine. The present study shows the temperature measurement of exit combustion gas as a function of a mixture ratio through the series of combustion tests of a fuel-rich gas generator with liquid oxygen and Jet A-1. The measurements of dynamic and static pressures, and combustion gas temperatures allowed the estimation of thermodynamic properties like a specific heat ratio, a gas constant, and a constant pressure specific heat of the combustion gas. The comparison of the experimental results with predictions made by interpolation parameters obtained from the modification of the chemical equilibrium code indicates that the interpolation method calibrated using the temperature measurements can be utilized as an effective tool for the initial design of a fuel-rich gas generator.

• Journal of Advanced Navigation Technology
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• v.23 no.2
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• pp.142-150
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• 2019

Muzzle Velocity is one of the most important measurement items for evaluation of ammunition. The muzzle velocity is defined as the velocity when the projectile leaves the muzzle. Particularly, since the muzzle velocity is closely related to the performance of the propellant, precise measurement of muzzle velocity is required. Doppler radar is used to measure the muzzle velocity, but the quality of Doppler radar signal depends on the test site environment. In this paper, a method to remove the clutter that degrades the signal quality of Doppler radar by improving the structure of the test site and the signal processing method is suggested. For the application of the improved signal processing method, a program for acquiring Doppler radar's raw Doppler data was created. Statistical verification of the velocity data obtained through the improvement of the test site structure and signal processing method proved that the proposed method is effective for the removal of clutter as compared with the existing method.

• Journal of Korea Water Resources Association
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• v.47 no.4
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• pp.307-319
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• 2014

Because of the rapid rising of water related disasters due to the global warming, the extreme design criteria of levee construction for severe flood has been applied in several developed countries such as USA and Netheland. In Korea, the national river restoration projects were carried out on 4 major rivers in recent several years. The projects consisted of riverbed dredge and levee reinforcement, and new construction have caused wide change of river environment. However, concrete countermeasures for levee safety and river management have not been suggested until now. Therefore, this study assesses the levee safety of Yulji levee located in Hoechon, Nakdong Basin, where the Levee Seepage Monitoring System installed. The stability of levee is assessed based on the simulation performed by SEEP/W(2D unsaturated seepage model) and the simulated results are compared with the observed data. The effects of the flood wave and levee shape on the levee safety are investigated through several simulations.