Skip to main content
SpringerLink
Log in

Experimental study on a transpiration cooling thermal protection system

  • Published:
Science China Technological Sciences Aims and scope Submit manuscript

Abstract

Transpiration cooling thermal protection systems (TPS) are investigated for potential applications in hypersonic and re-entry vehicles, which are subjected to the severe aerodynamic heating environment. In this paper a transpiration cooling thermal protection system was designed and manufactured, and an experiment platform with radiant heating at the bottom as heat source was developed. The cooling capacity of the transpiration cooling TPS was experimentally investigated. By combining transpiration cooling method with traditional TPS, the heat load capability of the TPS can be improved. The structure temperature with active cooling applied was much lower than that without active cooling applied under the same heat load as well as the heat load increased with active cooling than the one without active cooling for the same structure temperature. The experimental results showed that at 5800 s, the temperature of inner structure was 100°C with active cooling applied compared to 500°C without active cooling applied, then the temperature increased and reached to 360°C at 8300 s. Heat load of this transpiration cooling TPS can be increased by over 70% as compared to the passion one and the cooling capability of the transpiration TPS was about 1700 kJ/kg. The results can provide fundamental data for developing the transpiration cooling TPS.

This is a preview of subscription content, log in via an institution to check access.

Access this article

Log in via an institution

Price excludes VAT (USA)
Tax calculation will be finalised during checkout.

Instant access to the full article PDF.

Institutional subscriptions

Similar content being viewed by others

References

  1. Blosser M L, Chen R R, Schmidt I H, et al. Development of advanced metallic thermal protection system prototype hardware. J Spacecraft Rockets, 2004, 41(2): 183–190

    Article  Google Scholar 

  2. Blosser M L. Development of metallic thermal protection systems for the reusable launch vehicle. NASA TM, 1996. 1–22

  3. Blosser M L. Investigation of fundamental modeling and thermal performance issues for a metallic thermal protection system design. 40th Aerospace Sci Meeting&Exhibit. Reno, NV. AIAA 2002-0503: 1–21

  4. Myers D E, Martin C J, Blosser M L. Parametric weight comparison of advanced metallic, ceramic tile, and ceramic blanket thermal pro tection systems. NASA TM, 2000. 1–45

  5. Blosser M L. Advanced metallic thermal protection systems for reusable launch vehicles. Ph.D Dissertation. University of Virginia, 2000

  6. Buursink J. On the Development of a Cooled Metallic Thermal Protection System for Spacecraft. Ph.D Dissertation. Delft University of Technology, 2005

  7. Buursink J, Sudmeijer K J. Experiments on large enclosed model of enhanced radiation cooling system for metallic TPS. 13th International Space Planes and Hypersonics Systems and Technologyies, Capua, Italia. AIAA 2005-3369: 1–16

  8. Buursink J, Sudmeijer K J. Experimental studies of an enhanced radiation cooling system. Space Conference and Exhibit. San Diego, CA, AIAA 2004-5827: 1–13

  9. Lopes C. Concept design of an enhanced radiation cooling thermal protection system. M Sc Thesis Report, TU Delft, 2002

  10. Hong C Q, Zhang X H, Han J C, et al. Research on technology of transpiration cooling in thermal protection system(I) category of cooling methods, transpiration cooling materials and their basal theoretical models. Aerospace Mater Tech, 2005, 35(6): 7–12

    Google Scholar 

  11. Jiang P X, Yu L, Ren Z P. Influence of variable thermophysical proterties and thermal radiation on convection heat transfer in transpiration cooling. J Aerospace Power, 2004, 19(2): 184–190

    Google Scholar 

  12. Jiang P X, Ren Z P, Zhang Z F, et al. Numerical simulation of heat transfer in a transpiration cooled liquid rocket thrust chamber (II) numerical method and results. J Propul Tech, 1999, 20(4): 17–21

    Google Scholar 

  13. Rakow J F. Thermomechanical response of metal foam sandwich panels for structural thermal protection systems in hypersonic vehicles. Ph.D. Dissertation. University of Michigan, 2005

  14. Rakow J F, Waas A M. Size effects in metal foam cores for sandwich structures. AIAA J, 2005, 42(7): 1331–1337

    Article  Google Scholar 

  15. Rakow J F, Waas A M. Thermal Buckling of metal foam sandwich panels for actively cooled thermal protection systems. J Spacecraft Rockets, 2005, 42(5): 832–845

    Article  Google Scholar 

Download references

Author information

Authors and Affiliations

  1. Center for Composite Materials and Structure, Harbin Institute of Technology, Harbin, 150080, China

    Shuang Liu & BoMing Zhang

Authors
  1. Shuang Liu
    View author publications

    You can also search for this author in PubMed Google Scholar

  2. BoMing Zhang
    View author publications

    You can also search for this author in PubMed Google Scholar

Corresponding author

Correspondence to Shuang Liu.

Rights and permissions

Reprints and permissions

About this article

Cite this article

Liu, S., Zhang, B. Experimental study on a transpiration cooling thermal protection system. Sci. China Technol. Sci. 53, 2765–2771 (2010). https://doi.org/10.1007/s11431-010-4055-8

Download citation

  • Received:

  • Accepted:

  • Published:

  • Issue Date:

  • DOI: https://doi.org/10.1007/s11431-010-4055-8

Keywords

Search

Navigation