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Scale Reduction Methodology for Space Probe Aeroshell Testing
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English
Abstract
In the frame of technological activities for the study of Mars landing probes (MARSNET project), an innovative concept for the probe aeroshell was initially designed by Dassault under an ESA contract, based upon a mixed technology: an ablator-covered CFRP front-shield, surrounded by a C-SiC hot structure outer decelerator.
In order to get experimental validation of such a concept with a low-cost objective, a reduced scale test demonstrator of the full-scale concept has been designed.
A down-scaling methodology was therefore previously defined so as to keep as far as possible representativeness of the test conditions and results with respect to full scale design, while keeping the main design peculiarities for manufacturability demonstration.
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Citation
Verneuil, J. and Puech, J., "Scale Reduction Methodology for Space Probe Aeroshell Testing," SAE Technical Paper 951576, 1995, https://doi.org/10.4271/951576.Also In
References
- Scoon G.E.N. Whitcomb G.P. “Marsnet - A precursor to the surface exploration of Mars” IAF-92-0508
- Scoon G.E.N. Keller K. Bonnet C. “Aeroshell concepts for Mars landers” first ESA/ESTEC Workshop on Thermal Protection Systems May 1993
- Bonnet C. Puech J.F. Planas J.P. Berton B. “Aeroshell concepts trade-off for Mars landers” IAF-93-Q.1.378 October 1993
- Ostertag R. Trabandt U. “Fibre-reinforced ceramic components by filament winding for intermediate temperature applications” proceedings of ESA symposium “Advanced materials for lightweight structures” March 1992
- Verneuil J.C. Puech J.F. “Aeroshell compared design and analysis for Mars penetrators” SAE- 94-1370 Friedrichshafen June 1994