ABLATIVE PLASTIC CHARACTERIZATION IN SIMULATED MOTOR EXHAUST
Abstract
New chemical compositions and physical constructions of ablative material were exposed in a small scale, hig2 temperature Aeronutronic solid propellant rocket motor simulator and a liquid propellant (nitrogen tetroxide - 50 percent hydrazine and 50 percent unsymmetrical dimethylhydrazine) combustion gas environment to determine the potential usefulness of these materials for hyperenvironmental conditions associated with current and future solid dand liquid propellant motors. Material erosion and thermal insulation characteristics of the research nozzles were evaluated by comparisons of chamber pressure versus time data, erosion and resin degradation rates, and visual photographic data. Research nozzle specimens were exposed in two (2) groups to the exhaust environment of a simulated solid propellant having a flame temperature of 5800 F and being highly aluminized. Test Series 1 contained thirth (30) nozzle specimens and Test Series 2 contained twenty-four (24) specimens. Test results and preliminary specimen evaluation indicated that the Aeronutronic solid propellant simulator exhaust environment provided the specified exhaust environment with the required repeatable test screening characteristics to enable valid material evaluations. A total of seventy (70) nozzles were exposed to the exhaust environment of the liquid rocket motor (NTO/ 50-50). Several new ablative plastic composites were found to have ablative performance characteristics superior to the state-of-the-art carbon-phenolic and silica-phenolic composites.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1965
- Accession Number
- AD0476882
Entities
People
- C. S. Mayo
- R. E. Marcus
- S. L. Ostrow