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Numerical Study on Density Gradient Carbon–Carbon Composite for Vertical Launching System

  • Jin-Young Yoon
  • Chun-Gon Kim
  • Juhwan Lim
Original Paper

Abstract

This study presents new carbon–carbon (C/C) composite that has a density gradient within single material, and estimates its heat conduction performance by a numerical method. To address the high heat conduction of a high-density C/C, which can cause adhesion separation in the steel structures of vertical launching systems, density gradient carbon–carbon (DGCC) composite is proposed due to its exhibiting low thermal conductivity as well as excellent ablative resistance. DGCC is manufactured by hybridizing two different carbonization processes into a single carbon preform. One part exhibits a low density using phenolic resin carbonization to reduce heat conduction, and the other exhibits a high density using thermal gradient-chemical vapor infiltration for excellent ablative resistance. Numerical analysis for DGCC is performed with a heat conduction problem, and internal temperature distributions are estimated by the forward finite difference method. Material properties of the transition density layer, which is inevitably formed during DGCC manufacturing, are assumed to a combination of two density layers for numerical analysis. By comparing numerical results with experimental data, we validate that DGCC exhibits a low thermal conductivity, and it can serve as highly effective ablative material for vertical launching systems.

Keywords

Density gradient carbon–carbon Low thermal conductivity Transition density layer Numerical analysis 

References

  1. 1.
    Chung DDL (2001) Electromagnetic interference shielding effectiveness of carbon materials. Carbon 39(2):279–285.  https://doi.org/10.1016/S0008-6223(00)00184-6 MathSciNetCrossRefGoogle Scholar
  2. 2.
    Manocha LM (2003) High performance carbon–carbon composites. Sadhana 28(1):349–358.  https://doi.org/10.1007/BF02717143 CrossRefGoogle Scholar
  3. 3.
    Novoselov KS, Geim AK, Morozov SV, Jiang D, Zhang Y, Dubonos SV, Grigorieva IV, Firsov AA (2004) Electric field effect in atomically thin carbon films. Science 306(5696):666–669CrossRefGoogle Scholar
  4. 4.
    Geim AK, Novoselov KS (2007) The rise of graphene. Nat Mater 6(3):183–191.  https://doi.org/10.1038/nmat1849 CrossRefGoogle Scholar
  5. 5.
    Rani JR, Lim J, Oh J, Kim D, Lee D, Kim JW, Shin HS, Kim JH, Jun SC (2013) Substrate and buffer layer effect on the structural and optical properties of graphene oxide thin films. RSC Adv 3(17):5926–5936.  https://doi.org/10.1039/c3ra00028a CrossRefGoogle Scholar
  6. 6.
    Pulci G, Tirillo J, Marra F, Fossati F, Bartuli C, Valente T (2010) Carbon-phenolic ablative materials for re-entry space vehicles: manufacturing and properties. Compos A Appl Sci Manuf 41(10):1483–1490.  https://doi.org/10.1016/j.compositesa.2010.06.010 CrossRefGoogle Scholar
  7. 7.
    Tate JS, Gaikwad S, Theodoropoulou N, Trevino E, Koo JH (2013) Carbon, phenolic nanocomposites as advanced thermal protection material in aerospace applications. J Compos  https://doi.org/10.1155/2013/403656
  8. 8.
    Koo JH, Stretz H, Weispfenning JT, Luo Z, Wootan W (2004) nanocomposite rocket ablative materials: processing, microstructure, and performance. In: 45th AIAA/ASME/ASCE/AHS/ASC structures, structural dynamics and materials conference, Palm Springs, CA, USA, AIAA 2004–1996.  https://doi.org/10.2514/6.2004-1996
  9. 9.
    Fitzer E (1987) The future of carbon–carbon composites. Carbon 25(2):163–190.  https://doi.org/10.1016/0008-6223(87)90116-3 CrossRefGoogle Scholar
  10. 10.
    Moyer CB, Rindal RA (1968) 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-1061Google Scholar
  11. 11.
    Yeh Y (1990) Studies of the two-phase plume jet and Wall Erosion in a Vertical Launching System. Ph.D. Dissertation, Pennsylvania State University, University Park, PAGoogle Scholar
  12. 12.
    Yang BC, Cheung FB, Koo JH (1993) Modeling of one-dimensional thermomechanical erosion of high-temperature ablatives. J Appl Mech 60(4):1027–1032.  https://doi.org/10.1115/1.2900970 CrossRefGoogle Scholar
  13. 13.
    Shih YC, Cheung FB, Koo JH, Yang BC (2003) Numerical study of transient thermal ablation of high-temperature insulation materials. J Thermophys Heat Transf 17(1):53–61.  https://doi.org/10.2514/2.6733 CrossRefGoogle Scholar
  14. 14.
    Pizzo ME, Bey K, Glass DE (2016) Analysis of internal thermocouple data in carbon/carbon using inverse heat conduction methods. In: 54th AiAA aerospace sciences meeting, San Diego, CA, USA, AIAA 2016-0508.  https://doi.org/10.2514/6.2016-0508
  15. 15.
    Pizzo ME, Glass DE (2017) Characterization of a method for inverse heat conduction using real and simulated thermocouple data. In: 55th AIAA aerospace sciences meeting, Grapevine, TX, USA, AIAA 2017-0216.  https://doi.org/10.2514/6.2017-0216
  16. 16.
    Boyer CT, Talmy IG, Powers JW, Duffy JV, Haught DA (1993) Development and evaluation of erosion-resistant polymer matrix composite ablators. In: 31st Aerospace science meeting and exhibit, Reno, NV, USA, AIAA 93-0842.  https://doi.org/10.2514/6.1993-842
  17. 17.
    Koo JH, Miller MJ, Weispfenning J, Blackmon C (2011) Silicone polymer composites for thermal protection of naval launching system. J Spacecraft Rockets 48(6):904–919.  https://doi.org/10.2514/1.46534 CrossRefGoogle Scholar
  18. 18.
    Koo JH, Kneer MJ, Lin S, Schneider ME (1992) A cost-effective approach to evaluate high-temperature ablatives for military applications. Naval Eng J 104(3):166–177.  https://doi.org/10.1111/j.1559-3584.1992.tb02236.x CrossRefGoogle Scholar
  19. 19.
    Miller MJ, Koo JH, Siebenshuh JR (1995) Development of a scaled ducted launcher for ablative testing. In: 33rd Aerospace science meeting and exhibit, Reno, NV, USA, AIAA 95-0256.  https://doi.org/10.2514/6.1995-256
  20. 20.
    Ohlhorst CW, Vaughn WL, Ransone PO, Tsou HT (1997) Thermal conductivity database of various structural carbon–carbon composite materials. NASA TM 4787Google Scholar

Copyright information

© The Korean Society for Aeronautical & Space Sciences and Springer Nature Singapore Pte Ltd. 2018

Authors and Affiliations

  1. 1.Department of Aerospace EngineeringKAISTDaejeonRepublic of Korea
  2. 2.The 1st R&D Institute, Agency for Defense DevelopmentDaejeonRepublic of Korea

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