Journal of Aerospace System Engineering (항공우주시스템공학회지)

The Society for Aerospace System Engineering (항공우주시스템공학회)
권호 표지
DOI QR코드

DOI QR Code

Heat Transfer Characteristics of Thruster Controller According to Thickness of Thermal Barrier Coating

열차폐 코팅의 두께에 따른 추력 조절기의 열전달 특성 연구

  • Jang, Han Na (School of Aerospace and Mechanical engineering, Korea Aerospace University) ;
  • Lee, Ji Hoon (Department of Aerospace Engineering, Inha University) ;
  • Kwak, Jae Su (School of Aerospace and Mechanical engineering, Korea Aerospace University) ;
  • Cho, Jin Yeon (Department of Aerospace Engineering, Inha University) ;
  • Kim, Jae Hoon (School of Mechanical Engineering, Chungnam National University) ;
  • Ko, Jun Bok (Hanwha Corporation R&D Center) ;
  • Heo, Jun Young (Agency for Defense Development)
  • 장한나 (항공우주 및 기계공학과, 한국항공대학교) ;
  • 이지훈 (항공우주공학과, 인하대학교) ;
  • 곽재수 (항공우주 및 기계공학과, 한국항공대학교) ;
  • 조진연 (항공우주공학과, 인하대학교) ;
  • 김재훈 (기계공학부, 충남대학교) ;
  • 고준복 ((주)한화 종합연구소) ;
  • 허준영 (국방과학연구소)
  • Received : 2017.07.24
  • Accepted : 2017.08.28
  • Published : 2017.08.31
Download PDF
⟨ Previous Next ⟩

Abstract

In this study, the surface heat transfer coefficient of the 3D model of a thruster regulator in the high temperature and high pressure environment was estimated using the commercial CFD code. The thermal barrier coating (TBC) on the surface of the thruster regulator was modeled and the effect of the thickness of the TBC on the temperature of the thruster regulator was investigated. The thickness of the TBC was varied from $100{\mu}m$ to $500{\mu}m$. Results showed that the temperature of the surface and the inside the thruster regulator was lower for the thicker TBC case.

본 연구에서는 가변 추력기 3D 모델에 대해 상용 CFD 코드를 이용하여 고온 고압 환경에서의 추력 조절기 표면 열전달 계수를 예측하였다. 추력 조절기 표면에 열차폐코팅(TBC)을 모델링하였고, TBC 코팅의 두께가 추력조절기 내부 온도 분포에 미치는 영향을 연구하였다. TBC층의 두께는 $100{\mu}m{\sim}500{\mu}m$로 변화시켰다. 해석 결과, TBC층의 두께가 증가함에 따라 추력 조절기 표면과 내부 온도는 감소하는 경향을 보였다.

Keywords

References

  1. Kim, J.K. and Lee, Y.W., "The study on Determination Method of Initial Optimal Nozzle Expansion Ratio in Pintle Solid Rocket Motor," Journal of the Korean Society for Aeronautical & Space Science, Vol. 39, No.8, pp.744-749, 2011. https://doi.org/10.5139/JKSAS.2011.39.8.744
  2. Park, S.S., Moon, Y.G., and Kwak, J.S., "Numerical Analysis and 2-D Experiment of Heat Transfer Coefficient on the Pintle of a Controllable Thruster Nozzle," Journal of Aerospace System Engineering, Vol. 4, No. 4, pp.24-28, December, 2012
  3. Lee, J.H., Kim, Y.C., Park, S.H., Lim, S.T., Oh, S.J., Won, J.W., and Yun, E.Y., "A Study on the performance of variable thrust rocket motor by the pintle nozzle," 2012 KSPE Fall Conference, pp. 367-370
  4. Hwang, H.S. and Huh, H.I., "Experimental Study on Unsteady-state Characteristics of a Pintle Thruster with Variable Pintle Speeds," Journal of The Korean Aeronautical and Space Sciences, Vol.44, No. 3, 2016, pp.247-255 https://doi.org/10.5139/JKSAS.2016.44.3.247
  5. Noh, S.H., Kim, J.H., and Huh, H.I., "Performance Analysis of the Pintle Thruster Using 1-D Simulation -II : Unsteady State Characteristics," Journal of The Korean Society for Aeronautical and Space Sciences, Vol. 43, No. 4, 2015, pp. 311-317 https://doi.org/10.5139/JKSAS.2015.43.4.311
  6. Choi, J.S., Kim, D.Y., and Huh, H.I., "Thrust and Aerodynamic Load Characteristics fof an Internal Pintle Thruster," Journal of the Korean Society of Propulsion Engineers, Vol.21, No.3, pp.1-9, 2017 https://doi.org/10.6108/KSPE.2017.21.3.001
  7. X.Q. CaO, R.Vassen and D.Stoever, "Ceramic materials for thermal barrier coatings," Journal of the European Ceramic Society, Vol.24, 2004, pp.1-10 https://doi.org/10.1016/S0955-2219(03)00129-8
  8. Lee, J.H., Chang, H.B. and Ko, H., "A study of unsteady characteristics on the pintle nozzle," 2011 KSPE Fall Conference, 2011, pp.662-665
  9. L.H. Back, P.F. Massier, H.L. Gier, "Convective Heat Transfer in a Convergent-Divergent Nozzle," JET Propulsion Laboratory California Institute of Technology Pasadena, California, 1965
  10. Bae, J.Y., Bae, H.M., Ham, H.C. and Cho, H.H., "Heat Transfer on Supersonic Nozzle using Combined Boundary Layer Integral Model," Computational Structural Engineering Institute of Korea, Vol.30, 2017, pp.47-53 https://doi.org/10.7734/COSEIK.2017.30.1.47