Engineering approximations for Jovian entry

Details Engineering approximations for Jovian entry Engineering approximations for Jovian entry

Jun 1977

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1977thph.confr....l&link_type=abstract

American Institute of Aeronautics and Astronautics, Thermophysics Conference, 12th, Albuquerque, N. Mex., June 27-29, 1977, 9 p

Physics

Ablative Nose Cones, Atmospheric Entry, Computerized Simulation, Heat Shielding, Jupiter Probes, Ablation, Computer Programs, Convective Heat Transfer, Descent Trajectories, Flow Distribution, Jupiter Atmosphere, Radiative Heat Transfer, Silicon Oxides, Stagnation Point

Scientific paper

A code has been written to describe the behavior of an ablating heat shield throughout the entire maneuver into a planetary atmosphere. The code includes a trajectory computation for a variable mass, a computation of the heating history and distribution over the probe, ablation effects, indepth material response, and shape change. The code draws the initial and final shapes of the heat shield and computes its initial and final mass. Results are compared with those of other investigators, and solutions are obtained for a silica heat shield entering three model atmospheres of Jupiter. The effects of varying half cone angle and entry angle are examined as well as shape change effects. The so-called 'cusping effect' in the stagnation region is examined.

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