The Multi-Mission Earth Entry Vehicle project is developing an integrated tool called Multi Mission System Analysis for Planetary Entry Descent and Landing that will provide key technology solutions including mass sizing, aerodynamics, aerothermodynamics, and thermal and structural analysis for any given sample return mission. Thermal soak analysis and temperature predictions of various components including the payload container of the entry vehicle are part of the solution that this tool will offer to mission designers. The present paper focuses on the thermal soak analysis of an entry vehicle design based on the Mars Sample Return entry vehicle geometry and discusses a technical approach to develop parametric models for thermal soak analysis that will be integrated into the tool.
Thermal Soak Analysis of Earth Entry Vehicles
2012
16 pages
Report
No indication
English
Fluid Mechanics , Aerospace vehicles , Atmospheric entry , Mathematical models , Finite element method , Computational fluid dynamics , Soaking , Mars sample return missions , Thermal analysis , Aerothermodynamics , Computer aided design , Thickness , Grid generation(Mathematics) , Heat treatment , Aerodynamic heating
Thermal Soak Analysis of Earth Entry Vehicles
NTRS | 2012
|Thermal Soak Analysis of Earth Entry Vehicles
AIAA | 2012
|Parametric Thermal Soak Model for Earth Entry Vehicles
NTRS | 2013
|Numerical investigations of thermal soak
Tema Archive | 2007
|Experimental and Numerical Investigations of Thermal Soak
British Library Conference Proceedings | 2008
|