The first SH arp E dge F light EX periment of DLR has been established to demonstrate the feasibility of space vehicles with facetted Thermal Protection System (TPS). This study presents the thermodynamic behaviour of SHEFEX-I during the re-entry flight range of 60 km down to 20 km using a multidisciplinary simulation. Major effects like influence of the thermocouple position, overhang of the glue, and contact condition between the heat flux sensor and the TPS are analysed. The results of numerical calculations agree well with the experimental data.
Advanced Flight Analysis of SHEFEX-I
2010
9 Seiten
Aufsatz (Konferenz)
Englisch
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