Journal of the Korean Society of Propulsion Engineers (한국추진공학회지)

The Korean Society of Propulsion Engineers (한국추진공학회)
권호 표지
DOI QR코드

DOI QR Code

Thermal Response Modeling of Thermal Protection Materials and Application Trends of Commercial Codes for Flow-Thermal-Structural Analysis

내열재의 열반응 모델링 및 유동-열-구조해석의 상용코드 적용 동향

  • Hwang, Ki-Young (The 4th R&D Institute, Agency for Defense Development) ;
  • Bae, Ji-Yeul (The 4th R&D Institute, Agency for Defense Development)
  • Received : 2019.07.22
  • Accepted : 2019.08.26
  • Published : 2019.12.01
Download PDF
⟨ Previous Next ⟩

Abstract

The numerical analysis of ablative thermal protection systems (TPS) for solid rockets has been carried out with various in-house codes since the 1960s. However, the application scope of commercial codes has been expanded by adding subroutines and user-defined functions (UDF) to codes such as Fluent, Marc, and ABAQUS. In the past, the flow, thermal response and structural analysis of TPS have been performed using separate approaches. Recently, research has been conducted to interrelate them. In this paper, the thermal response characteristics of thermal protection materials, the in-house codes for thermal response analysis, and the research trends of flow-thermal-structure analysis of TPS using commercial codes were reviewed.

고체 로켓용 삭마성 내열 시스템의 수치 해석은 1960년대부터 다양한 In-house 코드로 수행되어 왔으나 Fluent, Marc, ABAQUS 등 상용코드에 서브루틴, UDF 등을 추가하여 해석 범위를 확장함으로써 상용코드의 활용 범위가 넓어지고 있다. 또한 예전에는 내열 시스템의 유동, 열반응과 구조해석을 각각 수행하였으나 근래에는 이들을 서로 연동하여 해석하는 연구들이 진행되고 있다. 본 논문에서는 내열재의 열반응 특성, 열반응 해석용 In-house 코드 그리고 상용코드로 내열 시스템의 유동, 열반응과 구조 해석을 수행한 연구동향을 고찰하였다.

Keywords

References

  1. Douglass, H.W., Collins, J.H., Ellis, R.A., and Keller, R.B., "Solid Rocket Motor Nozzle, Space Vehicle Design Criteria (Chemical Propulsion)," NASA SP-8115, 1975.
  2. Koo, J.H., Ho, D.W.H., and Ezekoye, O.A., "A Review of Numerical and Experimental Characterization of Thermal Protection Materials -Part I. Numerical Modeling," AIAA-2006-4936, July 2006.
  3. Ruffin, A., "Numerical Investigation of Nozzle Thermochemical Behaviour in Hybrid Rocket Motors," Master Thesis, University of Padua, Italy, Feb. 2015.
  4. Hwang, K.Y., Yim, Y.J., and Ham, H.C., “Effects of Aluminum Oxide Particles on the Erosion of Nozzle Liner for Solid Rocket Motors,” Journal of The Korean Society for Aeronautical and Space Sciences, Vol. 34, No. 8, pp. 95-103, 2006. https://doi.org/10.5139/JKSAS.2006.34.8.095
  5. Keswani, S.T. and Kuo, K.K., "An Aerothermochemical Model of Carbon-Carbon Composite Nozzle Recession," AIAA-83-0910, June 1983.
  6. Potts, R.L., “Application of Integral Methods to Ablation Charring Erosion, A Review,” Journal of Spacecraft and Rockets, Vol. 32, No. 2, pp. 200-209, 1995. https://doi.org/10.2514/3.26597
  7. Acharya, R. and Kuo, K.K., “Effect of Pressure and Propellant Composition on Graphite Rocket Nozzle Erosion Rate,” Journal of Propulsion and Power, Vol. 23, No. 6, pp. 1242-1254, 2007. https://doi.org/10.2514/1.24011
  8. Hwang, K.Y., Yim, Y.J., Ham, H. C., Kang, Y.G., and Bae, J.C., “Effects of Solid Propellant Gases on the Thermal Response of Nozzle Liner,” Journal of the Korean Society of Propulsion Engineers, Vol. 11, No. 2, pp. 26-36, 2007.
  9. Lemoine, L., "Solid Rocket Nozzle Thermostructural Behavior," AIAA-75-1339, Sep. 1975.
  10. Hwang, K.Y. and Park, J.K., “Characteristics and Development Trends of Heat-Resistant Composites for Flight Propulsion System,” Journal of The Korean Society for Aeronautical and Space Sciences, Vol. 47, No. 9, pp. 629-641, 2019. https://doi.org/10.5139/JKSAS.2019.47.9.629
  11. Shi, S., Gong, C., Liang, J., Fang, G., Wen, L., and Gu, L., “Ablation Mechanism and Properties of Silica Fiber-Reinforced Composite upon Oxyacetylene Torch Exposure,” Journal of Composite Materials, Vol. 50, No. 27, pp. 3853-3862, 2016. https://doi.org/10.1177/0021998315626504
  12. Bartz, D.R., "A Simple Equation for Rapid Estimation of Rocket Nozzle Convection Heat Transfer Coefficients," Jet Propulsion, pp. 49-51, 1957.
  13. Kays, W.M., Crawford, M.E., and Weigand, B., Convective Heat and Mass Transfer, 4th ed., McGraw-Hill Education, New York, U.S.A., Ch. 5, 2005.
  14. Murphy, A.J., Chu, E.K., and Kesswlring, J.P., "AFRL Graphite Performance Prediction Program, Vol. 1. Recommendations for a Standardized Analytic Procedure for MX Nozzle Throat Recession Calculation," ADA016720, 1975.
  15. Potts, R.L., "Hybrid Integral/Quasi-Steady Solution of Charring Ablation," AIAA-90-1677, June 1990.
  16. Ewing, M.E., Laker, T.S., and Walker, D.T., “Numerical Modeling of Ablation Heat Transfer,” Journal of Thermophysics and Heat Transfer, Vol. 27, No. 4, pp. 615-631, 2013. https://doi.org/10.2514/1.T4164
  17. Laturelle, F., Fiorot, S., and Wertheimer, T.B., "MSC.Marc-ATAS: Advanced Thermal Analysis Software for Modeling of Rocket Motors and Other Protection Systems," Worldwide Aerospace Conference and Technology Showcase, Toulouse, France, April 2002.
  18. Kendall, R.M., "An Analysis of the Coupled Chemically Reacting Boundary Layer and Charring Ablator, Part V: A General Approach to the Thermochemical Solution of Mixed Equilibrium-Nonequilibrium, Homogeneous or Heterogeneous Systems," NASA CR-1064, 1968.
  19. Moyer, C.B. and Rindal, R.A., "An Analysis of the Coupled Chemically Reacting Boundary Layer and Charring Ablator, Part II: Finite Difference Solution for the In-Depth Response of Charring Materials Considering Surface Chemical and Energy Balances," NASA CR-1061, 1968.
  20. Chen, Y.K. and Milos, F.S., “Ablation and Thermal Response Program for Spacecraft Heatshield Analysis,” Journal of Spacecraft and Rockets, Vol. 36, No. 3, pp. 475-483, 1999. https://doi.org/10.2514/2.3469
  21. Lee, E.M., et al., "ARBES Shape Change Code (ASCC 85Q*): Technical Report and User's Manual," Acurex Report FR-86-04/ATD, BMO TR-86-42, July 1986.
  22. Chen, Y.K. and Milos, F.S., "Two-Dimensional Implicit Thermal Response and Ablation Program for Charring Materials on Hypersonic Space Vehicles," AIAA-2000-0206, Jan. 2000.
  23. Chen, Y.K., Milos, F.S., and Gokcen, T., "Validation of a Three-Dimensional Ablation and Thermal Response Simulation Code," AIAA-2010-4645, June 2010.
  24. Ewing, M.E., Richards, G.H., Iverson, M.P., and Issac, D.A., "Ablation Modeling of a Solid Rocket Nozzle," 5th Ablation Workshop, Lexington, Kentucky, U.S.A., Feb. 2012.
  25. Amar, A.J., Oliver, A.B., Kirk, B.S., Salazar, G., and Droba, J., "Overview of the CHarring Ablator Response(CHAR) Code," 46th AIAA Thermophysics Conference, Washington, D.C., U.S.A., AIAA-2016-3385, June 2016.
  26. Lapp, P. and Quesada, B., "Analysis of Solid Rocket Motor Nozzle," 28th AIAA/SAE/ASME/ASEE Joint Propulsion Conference and Exhibit, Nashville, TN, U.S.A., AIAA-92-3616, June 1992.
  27. Wertheimer, T. and Laturelle, F., "Thermal Stress Analysis of TPS using Marc," Thermal & Fluids Analysis Workshop (TFAWS 2008), San Jose State University, San Jose, CA, U.S.A., Aug. 2008.
  28. Blades, E.L., Reveles, N.D., and Nucci, M., "Simulation of an Eroding Graphite Nozzle via a Fully Coupled Aero-Thermochemical-Elastic Framework," AIAA-2017-5021, 2017.
  29. Wang, Y., Risch, T.K., and Pasiliao, C.L., “Modeling of Pyrolyzing Ablation Problem with ABAQUS: A One-Dimensional Test Case,” Journal of Thermophysics and Heat Transfer, Vol. 32, No. 2, pp. 542-545, 2018.
  30. Meng, S., Zhou, Y., Xie, W., Yi, F., and Du, S., “Multiphysics Coupled Fluid/Thermal /Ablation Simulation of Carbon/Carbon Composites,” Journal of Spacecraft and Rockets, Vol. 53, No. 5, pp. 930-935, 2016. https://doi.org/10.2514/1.A33612
  31. Park, C., “Calculation of Stagnation-Point Heating Rates Associated with Stardust Vehicle,” Journal of Spacecraft and Rockets, Vol. 44, No. 1, pp. 24-32, 2007. https://doi.org/10.2514/1.15745
  32. Kang, Y.G., "1D-Thermal Reaction Analysis Program on Carbonaceous Nozzle Material (DAT-1C)," Software Registration No. 2011-01-129-005869, 29 Sep. 2011.
  33. Bae, J.Y., Kim, T.W, Kim, J.H., Ham, H.C., and Cho, H.H., “Conjugate Simulation of Heat Transfer and Ablation in a Small Rocket Nozzle,” Journal of Computational Structural Engineering Institute of Korea, Vol. 30, No. 2, pp. 119-125, 2017. https://doi.org/10.7734/COSEIK.2017.30.2.119
  34. Bae, J.Y., Hwang, K.Y. and Ham, H.C., "Development Report of Fluent-2C Software for Coupled Flow/Thermal Response Analysis of Rocket Nozzle," ADD Report, ADDR-421-191945, 2019.