Colloquium: Danny Tjokrosetio (ASM)

As Mars exploration is expected to increase in the near future, the challenge of entry, descent, and landing (EDL) imposed by the thin Martian atmosphere must be tackled. Lightweight approaches to entry vehicle design are critical to realize necessary EDL architectures. Heat shields integrating thermal and mechanical functions offer potential mass-saving solutions. Ceramic matrix composites (CMC) such as C/SiC, as well as ultra-high temperature ceramic matrix composites (UHTCMCs), are key materials to such thermal protection systems. This work explores the use of CMCs in designing a heat shield for a small Mars mission delivering a wind-driven rover. Various designs were evaluated, with the hot structure aeroshell concept showing minimal weight potential and versatility. Reference loads were obtained through a trajectory model, and finite element simulations were used to size the heat shield. For aeroshells of two sizes, comparisons were made between a baseline CMC skin material and a UHTCMC.

Supervisor: Ines Uriol Balbin