ABLATIVE PLASTIC CHARACTERIZATION IN SIMULATED MOTOR EXHAUST. PART III.
Abstract
New chemical compositions and physical constructions of ablative materials were exposed in three 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) the exhaust from a high-temperature Aeronutronic solid propellant rocket motor simulator, a nitrogen tetroxide (N2O4)-50 percent hydrazine and 50 percent unsymmetrical dimethylyhydrazine (50-50) liquid propellant environment, and a chlorine trifluoride (CTF)-hydrazine (N2H4) liquid propellant environment. 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. Eight nozzle specimens, comprising test series 1, were exposed to the exhaust environment of a storable liquid propellant rocket motor utilizing N2O4/50-50 at a chamber pressure of 700 psia. Twenty-five nozzle specimens (comprising test series 2) were exposed to the exhaust environment of a simulated solid propellant at a chamber pressure of 500 psia; flame temperature was 5800 F and the propellant was highly aluminized. Eight nozzle specimens, comprising test series 3, were exposed to the exhaust environment of another storable liquid propellant rocket motor utilizing CTF/N2H4 at a chamber pressure of 500 psia.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1967
- Accession Number
- AD0821639
Entities
People
- H. Blases
- J. Baetz
- S. L. Ostrow