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Launcher Vehicle Aerothermodynamics and Fairing Separation Altitude Effects on Payload Temperature
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 bydoi:10.13009/eucass2019-243 fatcat:b6pjykd435gorhuuu2oggsqcuy