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Ablative heat shield design for space shuttleAblator heat shield configuration optimization studies were conducted for the orbiter. Ablator and reusable surface insulation (RSI) trajectories for design studies were shaped to take advantage of the low conductance of ceramic RSI and high temperature capability of ablators. Comparative weights were established for the RSI system and for direct bond and mechanically attached ablator systems. Ablator system costs were determined for fabrication, installation and refurbishment. Cost penalties were assigned for payload weight penalties, if any. The direct bond ablator is lowest in weight and cost. A mechanically attached ablator using a magnesium subpanel is highly competitive for both weight and cost.
Document ID
19730022148
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Seiferth, R. W.
(Martin Marietta Corp. Denver, CO, United States)
Date Acquired
September 2, 2013
Publication Date
August 1, 1973
Subject Category
Thermodynamics And Combustion
Report/Patent Number
MCR-73-147
NASA-CR-132282
Accession Number
73N30880
Funding Number(s)
CONTRACT_GRANT: NAS1-11592
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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