HIGH TEMPERATURE RESISTANT MATERIALS FOR MISSILE PROPULSION SYSTEMS
Abstract
Five tantalum carbide nozzle inserts tested in the H-O rocket motor survived thermal shock although all specimens experienced varying degree of chemical erosion and four inserts were cracked. A molybdenum control specimen was superior to all of the above specimens. A TaC coating on graphite was ejected from the throat area after four seconds exposure. A hot pressing pellet study has been initiated to study TaC fabricated parameters. (Author, modified-PL).
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 30, 1961
- Accession Number
- AD0261043
Entities
Organizations
- Naval Ordnance Laboratory