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류병태(Byungtae Ryu),김준형(Junhyung Kim),황진옥(Jinok Hwang),안길환(Gilhwan Ahn) 한국추진공학회 2013 한국추진공학회 학술대회논문집 Vol.2013 No.12
압력카트리지는 화약으로 고온-고압의 가스를 형성하는 일종의 에너지 발생 장치이다. 압력카트리지는 너트, 볼트, 밸브, 사출시스템, Pressure-Actuated Pump, Switch 및 Pyrotechnic Cutter와 같은 피스톤 장치 등 항공 우주 산업 분야에서 다양하게 사용된다. 압력카트리지는 에너지원인 주장약의 재료에 따른 성능의 차이가 크다. 본 논문은 주장약 재료에 따른 압력카트리지 성능을 비교 하였다. The pressure cartridge is kind of energy generating device to form the high-pressure and high-temperature gas using pyrotechnic charge. The pressure cartridge is used in the military and aerospace industry such as nut, bolt, valve, ejection system, pressure-actuated pump, switch and pyrotechnic cutter. The pressure cartridge shows performance variation depending on the main charge, which is the energy source. This paper compares the main charge characteristics according to the main charge.
류병태(Byungtae Ryu),이도형(Dohyung Lee),류백능(Baekneung Ryoo),최홍석(Hongseok Choi) 한국추진공학회 2011 한국추진공학회 학술대회논문집 Vol.2011 No.11
본 논문은 우발적 화재에 노출되면 이상 온도를 감지하고, 자동으로 반응하여 추진제를 연소시킴으로써, 고체 추진기관의 위험 정도를 완화시키는 둔감 점화 장치의 반응을 연구한 결과이다. Kissinger 식으로 구한 둔감 점화 장치 신호 화약의 자동 점화 온도는 165.5℃이었지만, 추진기관에 장착하고 MIL-STD-2105D의 규정에 따라 수행한 완속 가열 시험에서는 약 140℃에서 연소 반응을 하였다. This paper describes on the study of mitigation technique in which a pyrosensor is automatically sensing the rate of risk of fire or explosion of solid rocket motor exposed to an unexpected fire and makes the rocket motor burn itself safely. SCO test was carried out with a rocket motor loaded with HTPB propellant, in which a thermal pyrosensor igniter was installed. The rocket motor in SCO test was located in an oven at 50℃ for 7 hours. The temperature was regulated to be elevated at the rate of 3.3℃ per hour. Results showed Type V(Burning) reaction in this SCO test.
류병태(Byungtae Ryu),이도형(Dohyung Lee),류백능(Baekneung Ryoo),최홍석(Hongseok Choi) 한국추진공학회 2012 한국추진공학회지 Vol.16 No.6
This paper describes the results of study on reaction of insensitive igniter in which a pyrosensor is automatically sensing the rate of risk of fire or explosion of solid rocket motor exposed to an unexpected fire and makes the rocket motor burn itself safely. The Slow Cook Off(SCO) test following the regulation of MIL-STD-2105D was carried out with a rocket motor loaded with HTPB propellant, in which a thermal pyrosensor igniter was installed. The auto-ignition temperature measured was approximately 140℃ and it corresponded to Type V(Burning) reaction in SCO test, while the temperature by Kissinger equation was calculated to be 165.5℃.
Mathematical and Experimental Study for Mixed Energetic Materials Combustion in Closed System
( Tae Yeon Kong ),( Byungtae Ryu ),( Gilhwan Ahn ),( Do Jin Im ) 한국화학공학회 2022 Korean Chemical Engineering Research(HWAHAK KONGHA Vol.60 No.2
Modelling the energy release performance of energetic material combustion in closed systems is of fundamental importance for aerospace and defense application. In particular, to compensate for the disadvantage of the combustion of single energetic material and maximize the benefits, a method of combusting the mixed energetic materials is used. However, since complicated heat transfer occurs when the energetic material is combusted, it is difficult to theoretically predict the combustion performance. Here, we suggest a theoretical model to estimate the energy release performance of mixed energetic material based on the model for the combustion performance of single energetic material. To confirm the effect of parameters on the model, and to gain insights into the combustion characteristics of the energetic material, we studied parameter analysis on the reaction temperature and the characteristic time scales of energy generation and loss. To validate the model, model predictions for mixed energetic materials are compared to experimental results depending on the amount and type of energetic material. The comparison showed little difference in maximum pressure and the reliability of the model was validated. Finally, we hope that the suggested model can predict the energy release performance of single or mixed energetic material for various types of materials, as well as the energetic materials used for validation.
양희원(Heewon Yang),방기복(Gibok Bang),류병태(Byungtae Ryu),김진환(JinHwan Kim) 한국추진공학회 2013 한국추진공학회 학술대회논문집 Vol.2013 No.12
파이로테크닉 점화기의 압력특성을 예측하기 위하여 이상기체 방정식을 적용한 이론식을 사용하여 점화기의 최대압력 및 최대압력 도달시간을 예측하였다. 이론식에서 총 연소시간, 연소가스 온도 등의 변수는 CEC code를 이용하여 근사적으로 구하고, 점화기 연소시험을 통하여 결정하였다. B/KNO3, MTV, Black powder 점화제 3종으로 점화기를 제작하여 압력 예측 및 연소시험을 실시하였다. 연소시험 및 최대압력 예측 결과, B/KNO3를 사용한 점화기의 경우 예측 결과와 실험값이 유사함을 확인하였으며, MTV의 경우 예측값이 실험값 보다 다소 높게 나타남을 확인하였다. Black Powder 와 금속성분이 혼합된 black powder의 경우 예측값과 실험값이 다른 결과로써 2종 혼합물을 사용한 점화기 압력특성 예측은 이론식 적용이 어렵다고 판단된다. In this study, we predict the pressure characteristic(delay time of maximum pressure and maximum pressure of igniter)by using analytical formula based on ideal gas equation . In the analytical formula, parameter of total burning time and temperature of ignition gas was searched by CEC code, and decided by ignition test. In igniter, Ignition agents were using B/KNO3, MTV, Black powder , predict the pressure characteristic and perform the ignition test. According to the prediction and test results, prediction results and test results are similar that using B/KNO3. In case of MTV, prediction results are higher than test results. From Black powder and ignition agent contain metal powder of predictions and test results are different, it is absolutely difficult to applying predict the pressure characteristic of igniter using Black powder and ignition agent contain Metal powder.
Mathematical Modeling of ZrKClO<sub>4</sub> Nano Particle Energy Release
Kong, Tae Yeon,Won, Yong Sun,Ryu, Byungtae,Ahn, Gilhwan,Im, Do Jin American Scientific Publishers 2017 Journal of Nanoscience and Nanotechnology Vol.17 No.11
<P>The ZrKClO4 particle is an energetic material used as a propellants in pyrotechnic applications. When hundreds of nm sized ZrKClO4 particles are ignited with electric shock, an oxygen atom which is bonded to an oxidizer (KClO4) obtains activation energy and becomes free oxygen atom resulting in the oxidation of Zr to form ZrO2. Energy generated from this oxidation reaction activates another near by oxygen atom and by a subsequent chain reaction the ZrKClO4 particles very rapidly release energy. Because this phenomenon occurs under anaerobic conditions, it is applied to combustion of spacecraft and rocket that need to be propelled under anaerobic conditions. Due to a growing interest in the aerospace industry, it is necessary to develop a more accurate energy release model of ZrKClO4 nanoparticles considering particle size and microscopic molecular structures in order to be used in various researched applications such as energy material performance evaluation tests and aging studies. In this work, a mathematical model describing the energy release of ZrKClO4 nano particles is suggested and compared with experiments.</P>
정혜흔(Hyeheun Jeong),김준형(Junhyung Kim),고승원(Seungwon Ko),류병태(Byungtae Ryu) 한국추진공학회 2016 한국추진공학회 학술대회논문집 Vol.2016 No.12
ZPP(Zirconium-Potassium Perchlorate)는 PMD(Pyrotechnic Mechanical Device)에 사용하는 1차 점화 장약의 일종이다. 용매에 녹아있는 바인더 성분을 석출시켜 부유해 있는 입자들을 유동상태에서 과립형태로 만들어 제조하는데 LabRAM Mixer를 이용하여 기계적 접촉을 하는 블레이드형 장비와 달리 공진현상을 이용하여 에너지를 전달시켜 입자를 제조한다. 본 연구를 통해 LabRAM Mixer의 조건 변화에 따라 제조한 입자의 특성을 평가하고 그 특성을 고찰하였다. ZPP(Zirconium-Potassium Perchlorate) is type of primary charge initiators for PMD(Pyrothchnic Mechanical Device) system. The binder component dissolved in the solvent is precipitated to suspended particles in the granules. The LabRAM Mixer uses resonance to transfer energy, unlike blade equipment that makes mechanical contact. In this study, the properties of the particles prepared of the LabRAM Mixer were evaluated according to the changes of the conditions.
김준형(Junhyung Kim),서태석(Taeseok Seo),고승원(Seungwon Ko),류병태(Byungtae Ryu) 한국추진공학회 2015 한국추진공학회 학술대회논문집 Vol.2015 No.5
착화기의 1차 점화장약으로 널리 사용되어지고 있는 ZPP(Zirconium/Potassium perchlorate)의 열분해 특성을 DSC를 사용하여 평가하였다. ZPP의 열분해반응에 대한 속도론적 파라미터를 결정하기 위하여, 다른 가열 속도를 갖고 수행된 DSC 결과들을 AKTS사의 Thermokinetics software를 사용하여 분석하였다. 결정된 속도론적 파라미터를 사용하여 계산된 모사값들은 실험적 결과들과 잘 일치함으로써, ZPP의 열분해과정에 대한 속도론적 모사의 유효성을 검증할 수 있었다. The thermal decomposition characteristics of the ZPP(Zirconium/Potassium perchlorate), widely used as a primary charge of initiators, were investigated by differential scanning calorimetry(DSC). The DSC results with different heating rates were elaborated with AKTS-Thermokinetics software for the determination of the kinetic parameters of the thermal decomposition of ZPP. There was good agreement between the experimental and the simulation curves, based on the determined kinetic parameters, which indicates the validity of the kinetic description of the thermal decomposition process of ZPP.