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Trajectory Based Heating and Ablation Calculations for MESUR Pathfinder AeroshellBased on the geometry of Mars Environment Survey (MESUR) Pathfinder aeroshell and an estimated Mars entry trajectory, two-dimensional axisymmetric time dependent calculations have been obtained using GIANTS (Gauss-Siedel Implicit Aerothermodynamic Navier-Stokes code with Thermochemical Surface Conditions) code and CMA (Charring Material Thermal Response and Ablation) Program for heating analysis and heat shield material sizing. These two codes are interfaced using a loosely coupled technique. The flowfield and convective heat transfer coefficients are computed by the GIANTS code with a species balance condition for an ablating surface, and the time dependent in-depth conduction with surface blowing is simulated by the CMA code with a complete surface energy balance condition. In this study, SLA-561V has been selected as heat shield material. The solutions, including the minimum heat shield thicknesses over aeroshell forebody, pyrolysis gas blowing rates, surface heat fluxes and temperature distributions, flowfield, and in-depth temperature history of SLA-561V, are presented and discussed in detail.
Document ID
20020006302
Acquisition Source
Ames Research Center
Document Type
Preprint (Draft being sent to journal)
Authors
Chen, Y. K.
(Eloret Corp. Palo Alto, CA United States)
Henline, W. D.
(NASA Ames Research Center Moffett Field, CA United States)
Tauber, M. E.
(NASA Ames Research Center Moffett Field, CA United States)
Arnold, James O.
Date Acquired
August 20, 2013
Publication Date
January 1, 1994
Subject Category
Fluid Mechanics And Thermodynamics
Funding Number(s)
PROJECT: RTOP 232-01-04
CONTRACT_GRANT: NAS2-14031
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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