한국항공우주학회지 (Journal of the Korean Society for Aeronautical & Space Sciences)

  • 제50권1호
  • /
  • Pages.21-30
  • /
  • 2022
  • /
  • 1225-1348(pISSN)
  • /
  • 2287-6871(eISSN)
한국항공우주학회 (The Korean Society for Aeronautical and Space Sciences)
권호 표지
DOI QR코드

DOI QR Code

스크램제트 엔진의 비시동 검출과 정량화 연구

A Study on Detection and Quantification of a Scramjet Engine Unstart

  • Kim, Hyunwoo (Dept. of Aerospace and Mechanical Engineering, Korea Aerospace University) ;
  • Seo, Hanseok (Dept. of Aerospace and Mechanical Engineering, Korea Aerospace University) ;
  • Kim, Jong-Chan (Bk21 FOUR Smart Drone Convergence, Korea Aerospace University, currently Korea Institute of Science and Technology Information) ;
  • Sung, Hong-Gye (School of Aerospace and Mechanical Engineering/Smart Air Mobility Engineering, Korea Aerospace University) ;
  • Park, Ik-Soo (Agency for Defense Development)
  • 투고 : 2021.10.05
  • 심사 : 2021.12.26
  • 발행 : 2022.01.01
PDF 다운로드
⟨ 이전 논문 다음 논문 ⟩

초록

스크램제트 엔진은 운용 중에 비시동이 발생하면 재시동이 거의 불가능하다. 그러므로 이에 대한 예측이 매우 중요하다. 본 연구에서는 격리부 출구에서의 배압을 조절함에 따라 나타나는 비시동 과정을 수치적으로 모사하였다. 비시동 데이터 검출은 벽면에서의 압력 데이터에 서포트 벡터 머신(SVM) 기법을 적용하여 흡입구의 시동과 비시동 데이터로 분류하였고, 시동과 비시동의 분류에 가장 적합한 압력 센서의 위치를 도출하였다. 또한 엔진의 시동과 비시동 경계를 분석하여 엔진이 비시동 되기까지의 여유(마진)을 정량화하였다.

The restart of scramjet engine is almost impossible in case its unstart happens during engine operation. Therefore, it is essential to prognosticate the scramjet engine unstart phenomena. A numerical simulation of a scramjet engine is conducted to investigate the unstart process of the scramjet engine by adjusting the backpressure at the isolator outlet to the engine analysis environment. The start and unstart of the engine are identified by applying a support vector machine (SVM) through the data measured by wall pressure so that the locations of the pressure sensors most suitable for the unstart detection are selected. And the operation conditions in which the engine is avoid to be unstarted are quantified to perceive the safety margin.

키워드

과제정보

본 연구는 방위사업청 국방과학연구소 연구사업(UE191011GD, UD210034SD)의 지원으로 수행되었습니다. 이에 대해 감사드립니다.

참고문헌

  1. Heo, Y., Moon, G. H. and Sung, H. G., "Investigation of Oswatisch Scheme for Maximum Total Pressure Recovery of Hypersonic Wedge-type Intakes," Journal of The Korean Society for Aeronautical and Space Sciences, Vol. 45, No. 12, 2017, pp. 2287~6871.
  2. Cox, C., Lewis, R., Pap, R., Glover, C., Priddy, K., Edwards, J., McCarty, C. and Wagner, E., "Prediction of Unstart Phenomena in Hypersonic Aircraft," AIAA Journal, Vol. 6, April 1995, pp. 3~7. https://doi.org/10.2514/3.55361
  3. Juntao, C., Nan, L., Kejing, X., Wen, B. and Daren, Y., "Recent research progress on unstart mechanism, detection and control of hypersonic inlet," Progress in Aerospace Sciences, Vol. 89, 2017, pp. 1~22. https://doi.org/10.1016/j.paerosci.2016.12.001
  4. Wilcox, D. C., Turbulence Modeling for CFD, 2ed Ed., DCW Industry, California, 2002, pp. 171~203.
  5. Sung, H. G., Kim, S. J., Yeom, H. Y. and Heo, J. Y., "On the Assessment of Compressibility Effects of Two-Equation Turbulence Models for Supersonic Transition Flow with Flow Separation," International Journal of Aeronautical and Space Science, Vol. 14, 2013, pp. 387~397. https://doi.org/10.5139/IJASS.2013.14.4.387
  6. Menter, F. R., Kuntz, M. and Langtry, R., "Ten Years Industrial Experience with the SST Turbulence Model," Turbulence Heat and Transfer, Vol. 4, 2003, pp. 625~632.
  7. Kim, J. C. and Sung, H. G., "Aerospace Problem Solving through Modular Multiphysics 3-D CFD code development," Proceedings of the Korea Society of Propulsion Engineers Spring Conference, Vol. 56, May 2021, pp. 203~206.
  8. Kitamura, K. and Hashimoto, A., "Reduced dissipation AUSM-family fluxes: HR-SLAU2 amd HR-AUSM+-up for high resolution unsteady flow simulations," Computers and Fluids, Vol. 126, 2016, pp. 41~57. https://doi.org/10.1016/j.compfluid.2015.11.014
  9. Schulein, E., "Development and Application of the thin of Flim Technique for Skin Friction Measurements in the Short Duration Hypersonic Wind Tunnel," AIAA Journal, Vol. 1, 2004, pp. 334~338. https://doi.org/10.2514/3.1533
  10. Manan, A. V. and David, F., "Mach 5 shock wave boundary layer interaction," NASA www.grc.nass.gov/WWW/windvalid/m5swbli/m5swbli.html, 2011.
  11. Wagner, J. L., Yuceil, K. B., Valdivia, A., Clemens, N. T. and Dolling, D. S., "Experimental Investigation of Unstart in an Inlet/Isolator Model in Mach 5 Flow," AIAA Journal, Vol. 47, 2009, pp. 1528~1542. https://doi.org/10.2514/1.40966
  12. Koo, H. S. and Venkatramanan, R. R., "Large-Eddy Simulation of a Supersonic Inlet-Isolator," AIAA Journal, Vol. 7, 2012, pp. 1596~1613.