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Trajectory-based heating analysis for the European Space Agency/Rosetta Earth Return VehicleA 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.
Document ID
19950037619
Document Type
Reprint (Version printed in journal)
Authors
Henline, William D. (NASA Ames Research Center Moffett Field, CA, United States)
Tauber, Michael E. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 16, 2013
Publication Date
May 1, 1994
Publication Information
Publication: Journal of Spacecraft and Rockets
Volume: 31
Issue: 3
ISSN: 0022-4650
Subject Category
SPACECRAFT DESIGN, TESTING AND PERFORMANCE
Distribution Limits
Public
Copyright
Other