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International Journal of Energetic Materials and Chemical Propulsion
ESCI SJR: 0.28 SNIP: 0.421 CiteScore™: 0.9

ISSN Imprimer: 2150-766X
ISSN En ligne: 2150-7678

International Journal of Energetic Materials and Chemical Propulsion

DOI: 10.1615/IntJEnergeticMaterialsChemProp.2020033869
pages 275-292

DEVELOPMENT OF ABLATIVE THERMAL RESPONSE MODELING OF EPDM-BASED THERMAL PROTECTION SYSTEMS

Ramin Shilav
RAFAEL Ltd., P.O. Box 2250 (M4), Haifa, 3102102, Israel
Savely Khosid
RAFAEL Ltd., P.O. Box 2250 (M4), Haifa, 3102102, Israel

RÉSUMÉ

A one-dimensional material response computer code has been developed for the ethylene-propylene-dien-monomer (EPDM)-based thermal protection system, designated as PARC. This surface ablation and pyrolysis code uses blowing wall boundary conditions and a dynamic coordinate system, and is coupled with computational fluid dynamics and thermodynamics programs' databases. A code-to-code comparison with NASA's PATO model shows very good agreement. Validation results are shown to be in good agreement with ablation gauges embedded in a subscale rocket motor. This modeling capability can improve modeling of ablative material performance in solid rocket motors.

RÉFÉRENCES

  1. Dec, J.A., Braun, R.D., and Laub, B., (2012) Ablative Thermal Response Analysis Using the Finite Element Method, J. Thermo-Phys. Heat Transf., 26(2), pp. 201-212.

  2. Incropera, F.P., Dewitt, D.P., Bergman, T.L., and Lavine, A.S., (2007) Fundamentals of Heat and Mass Transf., 6th ed., New York: John Wiley and Sons Inc., pp. 384-385.

  3. Lachaud, J., Cozmuta, I., and Mansour, N.N., (2010) Multi-Scale Approach to Ablation Modeling of Phenolic Impregnated Carbon Ablators, J. Spacecraft Rockets, 47(6), pp. 910-921.

  4. Lachaud, J., Magin, T.E., Cozmuta, I., and Mansour, N.N., (2011) A Short Review of Ablative-Material Response Models and Simulation Tools, 7th Aerothermodynamics Symp., European Space Agency, The Netherlands, pp. 1-8.

  5. Lachaud, J., Martin, A., Eekelen, T., and Cosmuta, I., (2012) Ablation Test-Case Series #2, Proc. 5th Ablation Workshop, Lexington, KY, pp. 1-9.

  6. Lachaud, J. and Mansour, N.N., (2014) Porous-Material Analysis Toolbox based on OpenFOAM and Applications, J. Thermo-Phys. Heat Transf., 28(2), pp. 191-202.

  7. Rindal, R.A., (1968) An Analysis of the Coupled Chemically Reacting Boundary Layer and Charring Ablator: Part 6: An Approach for Characterizing Charring Ablator Response with In-Depth Coking Reactions, NASA, Tech. Rep. NASA CR-1065.

  8. Russell, G.W. and Strobel, F., (2006) Modeling Approach for Intumescing Charring Heatshield Materials, J. Spacecraft Rockets, 43(4), pp. 739-749.

  9. Shilav, R. and Leitner, A., (2018) Modeling of Ablative Thermal Response of Low-Density Thermal Protection System, Proc. 58th Israel Annual Conf. on Aerospace Sciences, Haifa, Israel.

  10. Shilav, R., Leitner, A., and Gany, A., (2018) New Measurement Technique for Thermal Conductivity of Ablative Materials, Int. J. Energetic Mater. Chem. Propuls., 17(3), pp. 171-182.

  11. Scoggins, J.B. and Magin, T.E., (2014) Development of Mutation++: Multicomponent Thermodynamics and Transport Properties for IONized Gases Library in C++, 11th AIAA/ASME Joint Thermo-Physics and Heat Transfer Conf, Atlanta, GA, AIAA Paper 2014-2966.

  12. Theoretical Ablative Composite for Open Testing (TACOT), (2012) Version 2.2, 5th Ablation Workshop, Lexington, KY, from https://uknowledge.uky.edu/ablation/2012/2012_proceedings.pdf.


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