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Space Shuttle Main Engine nozzle thermal protection systemTwo of the three Space Shuttle Main Engine (SSME) nozzles are exposed to significant reentry aeroheating loads. To ensure reusability of the Nozzle Assembly, the nozzle primary structure must not exceed specific temperature limits. Due to the thermal, pressure, and dynamic flexing of the nozzle during a mission cycle, an appropriate insulating system must have significant flexibility. Recent missions have demonstrated nozzle reentry aeroheating rates and heat loads much higher than predictions, higher than the capability of the original insulating system. A new insulating system has been developed using similar materials in an aerodynamically 'smooth' shape to both reduce the incoming heating and increase radiation cooling.
Document ID
19850055519
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Nordlund, R. M.
(Rockwell International Corp. Rocketdyne Div., Canoga Park, CA, United States)
Date Acquired
August 12, 2013
Publication Date
June 1, 1985
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 85-1053
Accession Number
85A37670
Funding Number(s)
CONTRACT_GRANT: NAS8-27980
Distribution Limits
Public
Copyright
Other

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