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SCIENCE CHINA Technological Sciences, Volume 62 , Issue 8 : 1322-1330(2019) https://doi.org/10.1007/s11431-018-9476-2

Evaluation of numerical ablation model for charring composites

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  • ReceivedDec 3, 2018
  • AcceptedMar 1, 2019
  • PublishedJun 18, 2019

Abstract

Charring composites are widely used in the thermal protection system (TPS) to consume the intense aerodynamic heating during vehicle reentry. The ablation and thermal responses for the charring composites can be studied by using a numerical ablation model, in which the surface ablation and volume ablation could be taken into account. The coupling interactions among temperature, gas motion and interior pressure producing the pyrolysis gas could make the computation more complicated. A multi-physics model is developed to simulate the thermal response coupled with volume ablation and surface ablation. After studying four typical ablation cases, the model is validated, and then the heat transfer mechanisms in ablation are investigated. It is found that the viscous dissipation energy by the motion of pyrolysis gas can be neglected in the simulation. Also, the flow of pyrolysis gas plays an important role in the temperature response, especially under high heat flux condition.


Funded by

the National Natural Science Foundation of China(Grant,Nos.,11672089,&,11732002)

Natural Science Foundation of Heilongjiang Province

China(Grant,No.,A2017003)

and the Fundamental Research Funds for the Central Universities(Grant,No.,HIT.NSRIF.2017017)


Acknowledgment

This work was supported by the National Natural Science Foundation of China (Grant Nos. 11672089 & 11732002), the Natural Science Foundation of Heilongjiang Province, China (Grant No. A2017003), and the Fundamental Research Funds for the Central Universities (Grant No. HIT.NSRIF.2017017).


References

[1] Bianchi D, Nasuti F, Martelli E, et al. Navier-Stokes simulations of hypersonic flows with coupled graphite ablation. J Spacecr Rockets, 2010, 47: 554-562 CrossRef ADS Google Scholar

[2] Paglia L, Tirillò J, Marra F, et al. Carbon-phenolic ablative materials for re-entry space vehicles: Plasma wind tunnel test and finite element modeling. Mater Des, 2016, 90: 1170-1180 CrossRef Google Scholar

[3] Tran H K, Johnson C E, Rasky D J, et al. Phenolic impregnated carbon ablators (PICA) for discovery class missions. AIAA Paper No. 96-1911, 1996. Google Scholar

[4] Edquist K T, Hollis B R, Johnston C O, et al. Mars science laboratory heat shield aerothermodynamics: Design and reconstruction. J Spacecr Rockets, 2014, 51: 1106-1124 CrossRef ADS Google Scholar

[5] Dimitrienko Y I. Thermomechanics of Composite Structures under High Temperatures. Berlin: Springer, 2016. Google Scholar

[6] Moyer C B, Wool M R. Aerotherm Charring Material Thermal Response and Ablation Program, Version 3. Volume 1. Program Description and Sample Problems. Aerotherm Charring Material Thermal Response & Ablation Program Version, 1970. Google Scholar

[7] Chen Y K, Milos F S. Ablation and thermal response program for spacecraft heatshield analysis. J Spacecr Rockets, 1999, 36: 475-483 CrossRef ADS Google Scholar

[8] Li W, Huang H, Tian Y, et al. Nonlinear analysis on thermal behavior of charring materials with surface ablation. Int J Heat Mass Transfer, 2015, 84: 245-252 CrossRef Google Scholar

[9] Dec J A, Braun R D. Three-dimensional finite element ablative thermal response and design of thermal protection systems. J Spacecr Rockets, 2013, 50: 725–734. Google Scholar

[10] Lachaud J, Mansour N N. Porous-material analysis toolbox based on openFOAM and applications. J Thermophys Heat Transfer, 2014, 28: 191-202 CrossRef Google Scholar

[11] Lachaud J, Magin T E, Cozmuta I, et al. A short review of ablative-material response models and simulation tools. In: Proceedings of the 7th Aerothermodynamics Symposium. Bruggw: NTRS, 2011. Google Scholar

[12] Wang Y, Risch T K, Pasiliao C L. Modeling of pyrolyzing ablation problem with ABAQUS: A one-dimensional test case. J Thermophys Heat Transfer, 2018, 32: 544-548 CrossRef Google Scholar

[13] Wang Y, Zhupanska O I. Modeling of thermal response and ablation in laminated glass fiber reinforced polymer matrix composites due to lightning strike. Appl Math Model, 2017, 53: 118-131 CrossRef Google Scholar

[14] Zhu Y, Yi F, Meng S, et al. Multiphysical behavior of a lightweight ablator: Experiments, modeling, and analysis. J Spacecr Rockets, 2018, 55: 106-115 CrossRef ADS Google Scholar

[15] Hirata N, Nozawa S, Takahashi Y, et al. Numerical study of pyrolysis gas flow and heat transfer inside an ablator. Comput Thermal Scien, 2012, 4: 225-242 CrossRef Google Scholar

[16] Henderson J B, Wiecek T E. A mathematical model to predict the thermal response of decomposing, expanding polymer composites. J Compos Mater, 1987, 21: 373-393 CrossRef Google Scholar

[17] Anderson J D. Hypersonic and High-Temperature Gas Dynamics.2nd ed. New York: McGraw-Hill, 2006. Google Scholar

[18] Van Eekelen T, Lachaud J R, Martin A, et al. Definition of ablation test-case series #3. In: Proceedings of the 5th Ablation Workshop. Lexington, 2012. https://uknowledge.uky.edu/ablation/2012/Intercomparison/3/. Google Scholar

[19] COMSOL® Multiphysics Programming Reference Manual. V5.2. COMSOL Inc., 2017. Google Scholar

[20] Lachaud J, Martin A, Cozmuta I, et al. Ablation workshop test case. In: Proceedings of the 4th Ablation Workshop. Albuquerque, 2011. http://ablation2012.engineering.uky.edu/files/2012/02/Test_Case_1.pdf. Google Scholar

[21] Lachaud J, Martin A, Cozmuta I, et al. Ablation test-case series #2: Numerical simulation of ablative-material response: Code and model comparisons. In: Proceedings of the 4th AFOSR/SNL/NASA Ablation Workshop. Lexington: University of Kentucky, 2011. https://uknowledge.uky.edu/ablation/2012/Intercomparison/1/. Google Scholar

[22] Lachaud J, van Eekelen T, Bianchi D, et al. Theoretical Ablative Composite for Open Testing (TACOT). In: Proceedings of the Ablation Workshop: Code Comparison. “TACOT v3.0” (2014). https://uknowledge.uky.edu/ablation_code/4. Google Scholar

[23] White C, Scanlon T J, Brown R E. Permeability of ablative materials under rarefied gas conditions. J Spacecr Rockets, 2016, 53: 134-142 CrossRef ADS Google Scholar

[24] McDonald F B, Ferrando P, Heber B, et al. A comparative study of cosmic ray radial and latitudinal gradients in the inner and outer heliosphere. J Geophys Res, 1997, 102: 4643-4651 CrossRef ADS Google Scholar

[25] Weng H, Martin A. Numerical investigation of thermal response using orthotropic charring ablative material. J Thermophys Heat Transfer, 2015, 29: 429-438 CrossRef Google Scholar

[26] Shi S, Liang J, Lin G, et al. High temperature thermomechanical behavior of silica-phenolic composite exposed to heat flux environments. Compos Sci Tech, 2013, 87: 204-209 CrossRef Google Scholar

[27] Shi S, Li L, Liang J, et al. Surface and volumetric ablation behaviors of SiFRP composites at high heating rates for thermal protection applications. Int J Heat Mass Transfer, 2016, 102: 1190-1198 CrossRef Google Scholar

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