Launcher vehicle aerothermodynamics and fairing separation altitude effects on payload temperature

Alessandro Falchi, Lorenzo Gentile, Edmondo Minisci, Matteo Tirelli, Pierluigi Perugini

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Abstract

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 the different methodologies, and that an optimal theoretical fairing separation time can be found by minimizing the aerothermal fluxes incident on the payload.
Original languageEnglish
DOIs
Publication statusPublished - 1 Jul 2019
Event8th European Conference for Aeronautics and Space Sciences (EUCASS) - Madrid, Spain
Duration: 1 Jul 20194 Jul 2019

Conference

Conference8th European Conference for Aeronautics and Space Sciences (EUCASS)
CountrySpain
CityMadrid
Period1/07/194/07/19

Keywords

  • hypersonic aerothermodynamics
  • launcher vehicle
  • access to Space
  • fairing separation

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  • FOSTRAD: An advanced open source tool for re-entry analysis

    Falchi, A., Renato, V., Minisci, E. & Vasile, M., 30 Oct 2017. 15 p.

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  • Cite this

    Falchi, A., Gentile, L., Minisci, E., Tirelli, M., & Perugini, P. (2019). Launcher vehicle aerothermodynamics and fairing separation altitude effects on payload temperature. Paper presented at 8th European Conference for Aeronautics and Space Sciences (EUCASS), Madrid, Spain. https://doi.org/10.13009/EUCASS2019-243