한국추진공학회지 (Journal of the Korean Society of Propulsion Engineers)

  • 제24권6호
  • /
  • Pages.78-84
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  • 2020
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  • 1226-6027(pISSN)
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  • 2288-4548(eISSN)
한국추진공학회 (The Korean Society of Propulsion Engineers)
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준 일차원 다상 반응유동 기법을 이용한 케로신/과산화수소 액체 핀틀 추력기 성능해석 연구: Part II 추력기 성능 특성

Performance Analysis of Liquid Pintle Thruster Using Quasi-one-dimensional Multi-phase Reaction Flow: Part II. Thruster Performance Characteristics

  • Kang, Jeongseok (Department of Aerospace and Mechanical Engineering, Korea Aerospace University) ;
  • Bok, Janghan (Department of Aerospace and Mechanical Engineering, Korea Aerospace University) ;
  • Sung, Hong-Gye (School of Aerospace and Mechanical Engineering, Korea Aerospace University) ;
  • Kwon, Minchan (The 4th R&D Institute, Agency for Defense Development) ;
  • Heo, JunYoung (The 4th R&D Institute, Agency for Defense Development)
  • 투고 : 2020.07.27
  • 심사 : 2020.11.17
  • 발행 : 2020.12.31
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초록

본 논문에서는 Part I에 소개된 요소모델들을 통합하여 핀틀 추력기 성능 특성을 분석하였다. 성능해석 모델 검증을 위하여 케로신/과산화수소 액체 핀틀 추력기의 실험결과와 비교 분석하였다. 검증한 결과를 바탕으로 핀틀 추력기 내부의 비정상 열유동장의 물리적 특성을 분석하였으며 필름효과를 확인하였다. 또한 추력기의 형상인자와 작동인자가 성능특성에 미치는 영향을 파악하기 위하여 OAT 방법과 scatter plot 방법을 이용해 민감도 분석을 수행하였다. 액적직경, 필름유량, O/F비, 노즐목 직경의 4가지 인자를 이용해 특성속도, 연소실 압력, 비추력의 변화에 대한 영향을 관찰하였다.

The performance of pintle thruster is analyzed by using the pintle thruster performance analysis model which integrating the element models introduced in Part I. To verify the performance analysis, the results of the developed program are compared with the experimental data of kerosene/hydrogen peroxide liquid pintle thrusters. Based on the results, the characteristics of the pintle thruster are analyzed. The sensitivity analysis is performed to investigate the effect of thruster shape and operation parameters on performance characteristics using both OAT and scatter plot methods. The four performance parameters such as droplet diameter, film flow rate, O/F ratio, and nozzle throat diameter are evaluated to investigate their effects on characteristic speed, combustor pressure, and specific thrust.

키워드

과제정보

본 연구는 방위사업청 국방과학연구소 기초연구사업(2016-05-044)과 한국항공우주연구원이 지원하는 한국형발사체개발사업(2019M1A3A1A020-9859913)의 지원에 의해 수행되었습니다.

참고문헌

  1. Kang, J.S., Bok, J.H., Sung, H.G., Kwon, M.C. and Heo, J.Y., "Performance Anaylysis of Liquid Pintle Thruster Using Quasi-onedimensional Multi-phaase Reaction Flow - Part I Key Sub-model Validation," The Journal of the Korean Society of Propulsion Engineers, To be published.
  2. Lee, G.M. and Sung, H.G., "Threedimensional Effects of an Axi-symmetric Pintle Nozzle," Journal of the Korean Society of Propulsion Engineers, Vol. 22, No. 6, pp. 47-55, 2018. https://doi.org/10.6108/KSPE.2018.22.6.047
  3. Jeong, G.Y, Hong, J.S., Heo, J.Y., Sung, H.G., Yang, J.S. and Ha, D.S., "Thrust Characteristics of Through-type Pintle Nozzle at Operating Altitudes Conditions," Journal of the Korean Society of Propulsion Engineers, Vol. 20, No. 4, pp. 59-67, 2016. https://doi.org/10.6108/KSPE.2016.20.4.059
  4. Lee, G.B., Kim, J.C. and Sung, H.G., "The Analysis of Two-phase Flow in a Lean Direct Injection Gas-turbine Combustor," Journal of The Korean Society for Aeronautical and Space Sciences, Vol. 47, No. 3, pp. 204-211, 2019. https://doi.org/10.5139/JKSAS.2019.47.3.204
  5. Muss, A.J., Johnson, W.C., Kruse, W. and Cohn, K.R., "The Performance of Hydrocarbon Fuels with H2O2 in a Uni-element Combustor, "39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Las Vegas, N.V., U.S.A., AIAA 2003-4623, July. 2003.
  6. Han, D.H., Sung, H.G., Jang, S.G. and Ryu, B.T., "Parametric Analysis and Design Optimization of a Pyrotechnically Actuated Device," International Journal of Aeronautical & Space Science, Vol. 17, No. 3, pp. 409-422, 2016. https://doi.org/10.5139/IJASS.2016.17.3.409