Comprehensive Comparison of Different Integrated Thermal Protection Systems with Ablative Materials for Load-Bearing Components of Reusable Launch Vehicles

Economic viability of small launch vehicles, i.e., microlaunchers, is impaired by several factors, one which a higher dry to wet mass ratio as compared conventional size launchers. Although reusability may reduce cost, it can drive and/or unfeasibly high levels. In particular, for load-bearing components that are exposed convective heating during the aerothermodynamic phase re-entry, increase due presence thermal protection system (TPS) must be considered. Examples such aerodynamic drag devices (ADDs), extended re-entry. These should withstand mechanical loading, thermally protected avoid failure, and reusable. Ablative materials offer lightweight protection, but they represent an add-on structure rarely Similarly, TPS based on ceramic matrix composite (CMC) tiles additional mass. To tackle this issue, so-called integrated systems (ITPS) composed CMC sandwich structures were introduced in literature. The aim obtain at same time protective layer. However, comprehensive description real potential solutions ablative with corresponding sub-structures is, authors’ knowledge, not yet presented. Thus, design ADD, work aims holistically describe load bearing compare different solutions. Both preliminary designs discussed. Additionally, novel concept proposed, use change (PCMs) embedded within metallic additively manufactured lattice core. Such solution beneficial combination both specific stiffness mass-specific energy storage PCMs. study conducted reference first stage microlauncher analysed European Horizon-2020 project named Recovery Return Base (RRTB).