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Evaluation of Materials in Entry Heating SimulationThe basic objective in designing thermal protection systems is the provision of sufficient material to protect the vehicle structure and cargo from the severe heating encountered during entry into a planetary atmosphere. Conservative designs that may compromise the mission objective should be avoided. Ideally just enough material to ensure successful entry should be provided. The degree of success that is achieved by adhering to this philosophy is entirely dependent upon our knowledge of the entry environment and the manner in which the various materials respond to the environment.
Document ID
19690009637
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
William A Brooks, Jr
(Langley Research Center Hampton, United States)
Date Acquired
September 2, 2013
Publication Date
August 1, 1964
Publication Information
Publication: Proceedings of the Conference on the Role of Simulation in Space Technology, Part B
Publisher: National Aeronautics and Space Administration
Subject Category
Spacecraft Design, Testing and Performance
Report/Patent Number
NASA-CR-64950
NASA-CR-100138
Meeting Information
Meeting: Conference on the Role of Simulation in Space Technology
Location: Blacksburg, VA
Country: US
Start Date: August 17, 1964
End Date: August 21, 1964
Sponsors: National Aeronautics and Space Administration
Accession Number
69N18975
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Technical Review
NASA Technical Management
Keywords
Thermal Simulation
Material Testing
Ablating Material
Atmospheric Entry
Environment Simulation
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