Numerical Aero-shape Characterization of an Inflatable Heat Shield Re-entry Vehicle in the EFESTO-2 Project

The Inflatable Heat Shield (IHS) is considered a breakthrough solution to support the realization of innovative re-entry space missions as significantly increasing payload capability and space systems recovery. For this solution to become operational, a number of key technologies must be matured towards an appropriate level. In the frame of the EFESTO-2 project, structural and aerodynamic ground tests are planned to improve knowledge of this peculiar inflatable aerodynamic decelerator system. To reach this goal, a numerical study is carried out to simulate the maximum expected deformation level of the heat shield during the re-entry. Then, undeformed and deformed shapes of the heat shield are tested in the H2K and TMK wind tunnels. Post-test numerical rebuilding will follow this last step. This paper presents a pre-numerical investigation pointing out the definition of the test articles and the test campaigns, as well as post-numerical rebuilding with numerical-experimental cross-check.

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