Statistics – Computation
Scientific paper
Mar 1995
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1995jspro..32..225c&link_type=abstract
Journal of Spacecraft and Rockets (ISSN 0022-4650), vol. 32, no. 2, p. 225-230
Statistics
Computation
2
Ablation, Aerodynamic Heating, Computer Programs, Navier-Stokes Equation, Space Probes, Surface Properties, Computational Fluid Dynamics, Computerized Simulation, Conductive Heat Transfer, Heat Flux, Heat Transfer Coefficients, Temperature Distribution
Scientific paper
The Mars Pathfinder probe will enter the Martian atmosphere at a relative velocity of 7.65 km/s. The 2.65-m-diam vehicle has a blunted, 70-deg-half-angle, conical forebody aerobrake. Axisymmetric time-dependent calculations have been made using Gauss-Seidel implicit aerothermodynamic Navier-Stokes code with thermochemical surface conditions and a program to calculate the charring-material thermal response and ablation for heating analysis and heat-shield material sizing. The two codes are loosely coupled. The flowfield and convective heat-transfer coefficients are computed suing the flowfield code with species balance conditions for an ablating surface. The time-dependent in-depth conduction with surface blowing is simulated using the material response code with complete surface energy-balance conditions. This is the first study demonstrating that the computational fluid-dynamics code interfacing with the material response code can be directly applied to the design of thermal protection systems of spacecraft. The heat-shield material is SLA-561V. The solutions, including the flowfield, surface heat fluxes and temperature distributions, pyrolysis-gas blowing rates, in-depth temperature history, and minimum heat-shield thicknesses over the aeroshell forebody, are presented and discussed in detail. The predicted heat-shield mass is about 20 kg.
Chen Kuang Yao
Henline William D.
Tauber Michael E.
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