ABSTRACT
ABSTRACT: A corrugated-core sandwich panel can be used on the integrated thermal protection system of a hypersonic space shuttle. The outside walls of wings are designed as curved shapes to maintain a good aerodynamic performance. This paper proposes an effective laying method that lays the integrated thermal protection system on a curved wall based on conformal transformation. Then a heat transfer analysis is carried out for different cells that have corresponding heat flux curves. A transverse flow of heat energies is observed. The results show that the transverse heat transfer between the different cells may have a significant impact on temperature distribution. The safety of hypersonic vehicles can be improved owing to the temperature of the inner panel being a key failure index.
