The aeroheating environment of the Mars Reconnaissance Orbiter (MRO) has been analyzed using the Direct Simulation Monte Carlo and free-molecular techniques. The results of these analyses were used to develop an aeroheating database to be used for the pre-flight planning and the in-flight operations support for the aerobraking phase of the MRO mission. The aeroheating predictions calculated for the MRO include the heat transfer coefficient (C(H)) over a range of angles-of-attack, side-slip angles, and number densities. The effects of flow chemistry were also investigated. Flight heat flux data deduced from surface temperature sensors have been compared to pre-flight predictions and agree favorably.
Aeroheating Analysis for the Mars Reconnaissance Orbiter with Comparison to Flight Data
2006
8 pages
Report
Keine Angabe
Englisch
Aeroheating Analysis for the Mars Reconnaissance Orbiter with Comparison to Flight Data
Online Contents | 2007
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