ABLATIVE PLASTIC CHARACTERIZATION IN SIMULATED MOTOR EXHAUST.
Abstract
New chemical compositions and physical constructions of ablative materials were exposed to several rocket motor combustion gas environments to determine the potential usefulness of these materials for hyperenvironmental conditions associated with current and future solid and liquid propellant motors. These gas environments were (1) chlorine trifluoride (CTF) and hydrazine (N2H4), (2) nitrogen tetroxide (N2O4) and 50 percent hydrazine/50 percent unsymmetrical dimethlhydrazine (50-50) at three distinct conditions of chamber pressure and restart requirements, and (3) the exhaust from a high temperature solid propellant rocket motor simulator. 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. Test results from the four liquid propellant series indicated that the specified nominal test conditions were met, and enabled valid material evaluation. Test results and specimen evaluations also indicated that the solid propellant simulator provided the specified exhaust environment with the required repeatable test screening characteristics to enable valid material evaluation. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1968
- Accession Number
- AD0837638
Entities
People
- J. Baetz
- Jonathan Hall
- S. L. Ostrow