Trajectory-based heating analysis for the European Space Agency/Rosetta Earth Return Vehicle

Details Trajectory-based heating analysis for the European Space Agency/Rosetta Earth Return Vehicle Trajectory-based heating analysis for the European Space Agency/Rosetta Earth Return Vehicle

May 1994

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1994jspro..31..421h&link_type=abstract

Journal of Spacecraft and Rockets (ISSN 0022-4650), vol. 31, no. 3, p. 421-428

Statistics

Computation

Ablative Materials, Aerodynamic Heating, Atmospheric Entry, Ballistic Trajectories, Carbon-Phenolic Composites, Reentry Shielding, Reentry Vehicles, Spacecraft Shielding, Thermal Analysis, Ablation, Flow Distribution, Hyperbolic Trajectories, Temperature Effects

Scientific paper

A coupled, trajectory-based flowfield and material thermal-response analysis is presented for the European Space Agency proposed Rosetta comet nucleus sample return vehicle. The probe returns to earth along a hyperbolic trajectory with an entry velocity of 16.5 km/s and requires an ablative heat shield on the forebody. Combined radiative and convective ablating flowfield analyses were performed for the significant heating portion of the shallow ballistic entry trajectory. Both quasisteady ablation and fully transient analyses were performed for a heat shield composed of carbon-phenolic ablative material. Quasisteady analysis was performed using the two-dimensional axisymmetric codes RASLE and BLIMPK. Transient computational results were obtained from the one-dimensional ablation/conduction code CMA. Results are presented for heating, temperature, and ablation rate distributions over the probe forebody for various trajectory points. Comparison of transient and quasisteady results indicates that, for the heating pulse encountered by this probe, the quasisteady approach is conservative from the standpoint of predicted surface recession.

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