NASA NTRS · 19740020123
Development of high temperature materials for solid propellant rocket nozzle applications
Abstract
Aspects of the development and characteristics of thermal shock resistant hafnia ceramic material for use in solid propellant rocket nozzles are presented. The investigation of thermal shock resistance factors for hafnia based composites, and the preparation and analysis of a model of elastic materials containing more than one crack are reported.
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Manning, C. R., Jr., Lineback, L. D.. 1974-01-14. Development of high temperature materials for solid propellant rocket nozzle applications. https://ntrs.nasa.gov/citations/19740020123
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