Numerical aero-shape characterization of an Inflatable Heat Shield re-entry vehicle in the EFESTO-2 project

Abstract

Inflatable Heat Shields (IHS) are considered as a breakthrough solution to support realization of innovative re-entry space missions as a significant increase of 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 European 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, followed by post-tests numerical rebuilding. This paper presents pre-numerical investigation pointing out the definition of the test articles and the test campaigns, as well as post numerical rebuilding of TMK test experiments with numericalexperimental cross-checks.