Immersed finite element method for heat transfer analysis in multi-layered thermal protection systems.

Abstract

This paper presents a mathematical model for studying heat transfer in a spacecraft multi-layered thermal protection system, focusing on material properties and thickness optimization. The heat equation is solved using the immersed finite element method, which efficiently handles material discontinuities at layer interfaces. Simulations are conducted for a three-layer thermal protection system with materials such as carbon composites, ceramics, and insulating foams. Results show the impact of material selection and layer thickness on thermal performance, providing valuable insights for spacecraft design. The study demonstrates the effectiveness of the immersed finite element method for multi-material heat transfer problems in aerospace applications.