Modeling of Heat Transfer in Decomposable Materials of Thermal Protection Coating of Reentry Vehicle

Authors: Barinov D.Ya., Prosuntsov P.V. Published: 06.12.2016
Published in issue: #6(111)/2016  

DOI: 10.18698/0236-3941-2016-6-22-32

Category: Aviation and Rocket-Space Engineering | Chapter: Aerodynamics and Heat Transfer Processes in Aircrafts  
Keywords: mathematical model, reentry, vehicle, thermal protection, decomposable material, ablation

In this research we carried out mathematical modeling of the heat transfer in the element of thermal protection system (TPS) of the space reentry vehicle. One-dimensional formulation of the problem has been considered. The TPS element consists of three layers: a decomposable material, fibrous insulating material and a metal power structure. We developed physical and mathematical models of heat and mass transfer in the element of thermal protection. Furthermore, by means of the finite-element method in the software package Marc. Software Marc, we calculated the temperature fields during the descent to the Earth. We also obtained the carbonized layer depth and the temperature of the beginning of pyrolysis. Finally, we examined the influence of such parameters as emissivity of the TPS surface, thermal conductivity of a decomposable material in the area of medium and high temperatures, the activation energy of the material on the thermal state of the coating and the temperature of the power structure. Findings of the research show, that the biggest effect on the temperature of metal construction is provided by the activation energy and thermal conductivity in the area of medium temperatures, while the surface temperature is determined by emissivity of the surface. Thermal conductivity of a decomposable material in the area of high temperatures does not influence the temperature field of the TPS element.


[1] Nikitin P.V. Teplovaya zashchita [Thermal protection]. Moscow, MAI Publ., 2006. 512 p.

[2] Polezhaev Yu.V., Yurevich F.B. Teplovaya zashchita [Thermal protection]. Moscow, Energiya Publ., 1976. 392 p.

[3] Crouch R.K., Walberg G.D. An investigation on ablation behavior of AVCOAT 5026/39M over a wide range of thermal environments. NASA Technical Memorandum. 1969, no. X-1778. 36 p.

[4] Alifanov O.M., Budnik S.A., Nenarokomov A.V., Netelev A.V. Identification of the mathematical models of heat transfer in destruction materials. Teplovye protsessy v tekhnike [Thermal Processes in Engineering], 2011, vol. 3, no. 8, pp. 338-347 (in Russ.).

[5] Nikitin P.V., Sotnik E.V. Features of the mechanism of destruction glass-reinforced heat-shielding materials at variable parameters thermal exposure. Teplovye protsessy v tekhnike [Thermal Processes in Engineering], 2011, vol. 3, no. 8, pp. 348-359 (in Russ.).

[6] Chen Y.-K., Milos F.S. Ablation and thermal response program for spacecraft heatshield analysis. Journal of Spacecraft and Rockets, 1999, vol. 36, no. 3, pp. 475-483. DOI: 10.2514/2.3469

[7] Dec J.A., Braun R.D., Lamb B. Ablative thermal response analysis using the finite element method. Journal of Thermophysics and Heat Transfer, 2012, vol. 26, no. 2, pp. 201-212. DOI: 10.2514/1.T3694

[8] Zemlyanskiy B.A., Lunev V.V., Timoshenko V.P., et al. Some heat exchange problems of hypersonic aircraft of gliding descent. Trudy NPO "Molniya", 1985, no. 1, pp. 34-61 (in Russ.).

[9] Alifanov O.M., Artyukhin E.A., Nenarokomov A.V. Obratnye zadachi v issledovanii slozhnogo teploobmena [Inverse problems in complex heat exchange investigation]. Moscow, Yanus-K Publ., 2009. 300 p.

[10] Isaev K.B. Teplofizicheskie kharakteristiki materialov v shirokikh diapazonakh temperatur i skorostey nagreva [Material thermophysical properties in wide temperature band]. Kiev, Kupriyanova Publ., 2008. 240 p. (in Russ.).

[11] MSC Marc Volume A: Theory and user information. MSC Software Corporation, 2013. 876 p.

[12] Wertheimer T.B., Laturelle F. Thermal decomposition analysis of rocket motors and other thermal protection systems using MSC. Marc-ATAS. Proc. 14-th Thermal & Fluid Analysis Workshop, 2003. 16 p.

[13] Davis B.A. International Space Station (ISS) Soyuz vehicle descent module evaluation of thermal protection system (TPS) penetration characteristics. NASA Technical Report, 2013, JSC-66527. 396 p.

[14] GOST 4401-81. Atmosfera standartnaya. Parametry [State standard 4401-81. Standard atmosphere. Parameters]. Moscow, Izd-vo standartov Publ., 1981. 180 p.