Aeroheating Analysis for the Mars Reconnaissance Orbiter with Comparison to Flight Data | Zendy

Derek S. Liechty | Zendy

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Aeroheating Analysis for the Mars Reconnaissance Orbiter with Comparison to Flight Data

Author(s) -

Derek S. Liechty

Publication year - 2007

Publication title -

journal of spacecraft and rockets

Language(s) - English

Resource type - Journals

SCImago Journal Rank - 0.758

H-Index - 79

eISSN - 1533-6794

pISSN - 0022-4650

DOI - 10.2514/1.25843

Subject(s) - orbiter , aerospace engineering , spacecraft , mars exploration program , spacecraft design , missile , space shuttle , systems engineering , space (punctuation) , exploration of mars , aeronautics , astrobiology , space exploration , computer science , engineering , physics , operating system

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.

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