Measurement of Rocket Nozzle Surface Recession using Spectrographic Techniques
Final rept. 15 Mar 1971-31 Jul 1972
UNITED TECHNOLOGY CENTER SUNNYVALE CA
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The objective of this program was to design, analyze, and evaluate experimentally the surface recession of ablative materials using spectrographic techniques. This program was accomplished in two phases. The first phase was the design, analysis, and development of a containment system for the tracer elements. The second phase was the demonstration of the feasibility of that system during static firings in two rocket nozzles, one fabricated from carbon-phenolic and the other from silica-phenolic with a codeposited silicon carbidepyrolytic-graphite throat insert. Laboratory tests were conducted with a plasma-arc torch to verify the capsule design. The capsules, with thermocouples, were then tested in a solid rocket motor at a pressure of 800 psi with 16- aluminized polybutadiene-acrylic acid-acrylonitrile propellant. The test results showed poor correlation between the ablation as indicated by thermocouples and that indicated by detection of the tracer salts. This report describes the various program activities from initial tracer selection and configuration selection to final test firing demonstration and analysis of test results.
- Solid Propellant Rocket Engines