Title:
Computation of temperature distribution in the integrated thermal protection system for reusable launch vehicle
Authors:
- Edyta Hetmaniok
- Rafal Brociek
- Damian Slota
Published in:
(2024). ECMS 2024, 38th Proceedings
Edited by: Daniel Grzonka, Natalia Rylko, Grazyna Suchacka, Vladimir Mityushev, European Council for Modelling and Simulation.
DOI: http://doi.org/10.7148/2024
ISSN: 2522-2422 (ONLINE)
ISSN: 2522-2414 (PRINT)
ISSN: 2522-2430 (CD-ROM)
ISBN: 978-3-937436-84-5
ISBN: 978-3-937436-83-8 (CD) Communications of the ECMS Volume 38, Issue 1, June 2024, Cracow, Poland June 4th – June 7th, 2024
DOI:
https://doi.org/10.7148/2024-0261
Citation format:
Edyta hetmaniok, Rafal brociek, Damian slota (2024). Computation of Temperature Distribution in the Integrated Thermal Protection System for Reusable Launch Vehicle, ECMS 2024, Proceedings Edited by: Daniel Grzonka, Natalia Rylko, Grazyna Suchacka, Vladimir Mityushev, European Council for Modelling and Simulation. doi:10.7148/2024-0261
Abstract:
In this paper the mathematical model of three-layer system representing the integrated thermal protection system, possible to use in the reusable launch vehicle, is discussed. In each layer the distribution of temperature is described with the aid of the heat conduction equation, completed by the interface boundary conditions properly defined at the interfaces between adjacent layers. On the outer surface the boundary condition of the second kind is assumed, including the aerothermal heat flux generated at NASA Langley Research Center. Whereas on the inner surface the boundary condition of the first kind is defined. Moreover, the model allows the variation of material parameters depending on the temperature. The numerical problem is solved by using the implicit scheme of the finite difference method. The procedure is executed for various space-time grids and the results of this research confirm the convergence of the scheme when the grid dense increases.
Full text:
Download full text