The first part of this research investigates and compares VEGA launcher vehicle aerothermodynamics during a nominal ascent trajectory simulated by means of Direct Simulation Monte Carlo and hypersonic local panel methods. In the second part of the work, the coupled aerothermal-structural simulation of the ascent phase up to 250s was performed, studying the heat transfer between the payload fairing and a dummy payload. The results have shown a good match among the aerothermal fluxes estimated by

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... the different methodologies, and that an optimal theoretical fairing separation time can be found by minimizing the aerothermal fluxes incident on the payload.