Defining Ablative Thermal Protection System Margins for Planetary Entry Vehicles
Author:
Affiliation:
1. NASA Ames Research Center
2. ERC, Inc.
3. Lockheed Martin Corporation
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.2011-3757
Reference31 articles.
1. NASA's In-Space Propulsion Technology Program: Overview and Update
2. Computational Aerothermodynamic Design Issues for Hypersonic Vehicles
3. Avco Corporation, "Ablation Handbook, Entry Materials Data and Design," Technical Report AFML-TR-66-262, Sep. 1966.
4. Effects of environmental and ablator performance uncertainties on heat-shielding requirements for hyperbolic entry vehicles.
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