抄録
This paper presents a thermal p-version multidimensional finite element for ablative materials which can be applied to the simple thermal structural analysis of an atmospheric re-entry vehicle's ablative thermal protection system. The element is integrated into the element library of a multidisciplinary optimization analysis system developed by the Japan Aerospace Exploration Agency's Aerospace Research and Development Directorate. As with a general thermal shell element, a user of this system can set the initial thickness of the virgin layer as a parameter instead of by coordinates, allowing parametric studies to be easily conducted. The element can be laminated with other general thermal element models; for example, an aluminum primary structure-strain isolation pad-ablative material shell configuration typical of a re-entry vehicle thermal protection system.
