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RISS 인기검색어
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- 저자 : 장동욱(Dongwuk Jang) (검색결과 5 건)
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장동욱(Dongwuk Jang),조성권(Sungkwon Jo),조황래(Hwangrae Cho),방정석(Jeongseok Bang),권세진(Sejin Kwon) 한국추진공학회 2011 한국추진공학회 학술대회논문집 Vol.2011 No.11
2,500 N급 과산화수소/케로신 이원 추력기의 성능 향상 및 다양한 임무에 적용하기 위하여 재생냉각의 적용가능성을 검토하였다. 1-D 계산을 통해 과산화수소를 냉각제로 하는 경우에 대한 계산을 수행하였다. 설계된 재생냉각 연소기의 노즐 목에서의 열 유속은 18~20 MW/m2 로 예측되었으며, 그에 따른 유로의 너비는 2.5 mm 높이는 0.45 mm로 설계 되었다. 설계된 유로형상을 바탕으로 냉각 유로 내에서의 압력강하를 예측하기 위한 평판형 모델을 제작하여 실험을 진행하였고, 수치해석결과와 비교를 수행하였다. 그 결과, 수치해석과 실험결과와의 최대 오차는 약 13%, 평균 오차는 약 5%로 계산되었다. Applicability of regenerative cooling in 2,500 N-class bipropellant thruster using hydrogen peroxide and kerosene was considered for improvement performance and application in various missions. Calculation was performed by one dimensional approach using hydrogen peroxide as a coolant. In designed regenerative cooling thruster, heat flux at nozzle throat was estimated at 18 ~ 20 MW/m2. Designed cooling channel width and height were 2.5 mm and 0.5 mm, respectively. Based on designed cooling channel configuration, flat plate model was manufactured and tested for estimation of pressure drop in cooling channel, and CFD analysis was compared with the test result. The maximum error between CFD analysis and experimental result was approximately 13% and average error was approximately 5%.
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특성길이 변화에 따른 H<SUB>2</SUB>O<SUB>2</SUB>/Kerosene 이원추진제 로켓 엔진의 성능평가
조성권(Sungkwon Jo),장동욱(Dongwuk Jang),김종학(Jonghak Kim),윤호성(Hosung Yoon),권세진(Sejin Kwon) 한국추진공학회 2010 한국추진공학회 학술대회논문집 Vol.2010 No.11
고농도 과산화수소를 이용하는 1,200 N 급 이원추진제 로켓 엔진 개발을 위한 기존 연구와 더불어, 특성길이의 영향 및 추력 측정을 통한 실질적인 성능을 평가하였다. 특성길이는 0.95, 1.07과 1.20 m, 총 3가지 경우에 대하여 실험을 수행하였으며, 특성길이의 증가에 따라 C<SUP>*</SUP> 효율 및 Isp 효율 모두 증가함을 확인하였다. 설계 당량비에서의 최대 C<SUP>*</SUP> 및 Isp 효율은 각각 98.4%와 93.1%로 측정되었다. 엔진 성능 평가 결과를 바탕으로 분해된 과산화수소를 이용한 엔진에서의 최적 특성길이를 제안하고, 설계 당량비에서의 추력 및 비추력 효율을 이용하여 진공에서의 엔진성능을 예측하여 보았다. 그 결과, 지상 218.4 s, 진공 253.3 s의 비추력과, 진공 추력 1035.3 N의 성능을 예상할 수 있다. In addition to the previous study for development of a 1,200 N-class bipropellant rocket engine with concentrated hydrogen peroxide, the effect of characteristic length and thrust measurement were experimentally evaluated. Tests with characteristic lengths of 0.95, 1.07, and 1.20 m were performed and C<SUP>*</SUP> and Isp efficiencies were increased as increasing characteristic length. The maximum C<SUP>*</SUP> and Isp efficiencies were 98.4% and 93.1% respectively. Based on the evaluation of the designed engine, the optimized characteristic length was proposed in using the engine adapted decomposed hydrogen peroxide and the engine performance at vacuum-level was evaluated using thrust and Isp efficiency at the designed equivalence ratio. As a result, 218.4 s at sea-level, 253.3 s at vacuum-level, and vacuum thrust of 1035.3 N can be estimated.
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블렌딩 기법을 적용한 과산화수소 추진제의 저장성 및 재료 적합성 평가
이정섭(Jeongsub Lee),장동욱(Dongwuk Jang),권세진(Sejin Kwon) 한국추진공학회 2011 한국추진공학회 학술대회논문집 Vol.2011 No.11
친환경 추진제인 과산화수소의 성능 향상을 위해 블렌딩 기법을 적용하였다. 90 wt.% 과산화수소에 독성이 낮은 에탄올을 블렌딩 하였으며, 저장성 평가 결과 연료에 의한 저장성 저하는 나타나지 않았다. 재료 적합성 및 내열 평가 결과 Inconel X750과 Topheat A가 높은 적합성과 내열 특성을 보였으며, SUS 316L 역시 적합성이 우수하였다. 내열 특성 향상을 위해 Al2O3, Y2O3, ZrO2를 코팅 후 내구성 평가를 수행한 결과, Y2O3 코팅은 사용이 부적합하였으며, 재료의 사용 가능 온도가 코팅의 접착성과 관련이 있음을 확인하였다. 블렌딩 기법을 통한 성능 향상을 확인하기 위해 추력기 실험을 진행하였으며, 실험 결과 반응기 온도가 870 ℃로, 90 wt.% 과산화수소의 단열 분해 온도인 760 ℃ 보다 높음을 확인하였다. Blending method was applied to increase the performance of hydrogen peroxide which is called green propellant. 90 wt.% hydrogen peroxide was blended with ethanol which is less toxic fuel, and there was no storability decrease due to fuel addition. Inconel X750 and Tophet A showed good compatibility and high heat resistance, and SUS 316L was compatible. Al2O3, Y2O3, and ZrO2, were coated on the material to improve heat resistance, and it was proved from endurance test that Y2O3 coating is not suitable and adhesive strength between coating and material is related with allowable temperature of material. Thruster test was performed to confirm the performance increase by blending method, and chamber temperature was 870 ℃ which is higher than 760 ℃ that is adiabatic chamber temperature of 90 wt.% hydrogen peroxide.
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특성길이 변화에 따른 H₂O₂/Kerosene 이원추진제 로켓 엔진의 성능평가
조성권(Sungkwon Jo),장동욱(Dongwuk Jang),김종학(Jonghak Kim),윤호성(Hosung Yoon),권세진(Sejin Kwon) 한국추진공학회 2011 한국추진공학회지 Vol.15 No.3
In addition to the previous study for development of a 1,200 N-class bipropellant rocket engine with concentrated hydrogen peroxide, the effect of characteristic length and thrust measurement were experimentally evaluated. Tests with characteristic lengths of 0.95, 1.07, and 1.20 m were performed and C<SUP>*</SUP> and Isp efficiencies were increased as increasing characteristic length. The maximum C<SUP>*</SUP> and Isp efficiencies were 98.4% and 93.1% respectively. Based on the evaluation of the designed engine, the optimized characteristic length was proposed in using the engine adapted decomposed hydrogen peroxide and the engine performance at vacuum-level was evaluated using thrust and Isp efficiency at the designed equivalence ratio. As a result, 218.4 s at sea-level, 253.3 s at vacuum-level, and vacuum thrust of 1035.3 N can be estimated.
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블렌딩 기법을 적용한 과산화수소 추진제의 저장성 및 재료 적합성 평가
이정섭(Jeongsub Lee),장동욱(Dongwuk Jang),권세진(Sejin Kwon) 한국추진공학회 2012 한국추진공학회지 Vol.16 No.5
Blending method was applied to increase the performance of hydrogen peroxide which is called green propellant. 90 wt.% hydrogen peroxide was blended with ethanol which is less toxic fuel, and there was no storability decrease due to fuel addition. Inconel X750 and Tophet A showed good compatibility and high heat resistance, and SUS 316L was compatible. Al<sub>2</sub>O<sub>3</sub>, Y<sub>2</sub>O<sub>3</sub>, and ZrO<sub>2</sub>, were coated on the material to improve heat resistance, and it was proved from endurance test that Y<sub>2</sub>O<sub>3</sub> coating is not suitable and adhesive strength between coating and material is related with allowable temperature of material. Thruster test was performed to confirm the performance increase by blending method, and chamber temperature was 870℃ which is higher than 760℃ that is adiabatic chamber temperature of 90 wt.% hydrogen peroxide.
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