RESEARCH ON ABLATIVE PLASTIC CHARACTERIZATION IN SIMULATED MOTOR EXHAUST. PART 2
Abstract
New chemical compositions and physical constructions of ablative materials were exposed in a small scale, high 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 and 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. This document is the second yearly summary technical report covering test series four and five, which included forty-nine (49) research nozzle specimens. Thirty (30) research nozzle specimens, comprising test series 4, were exposed to the exhaust environment of a simulated solid propellant having a flame temperature of 5800 F and being highly aluminized. Nineteen (19) nozzles, comprising test series 5, were exposed to the exhaust environment of a storable liquid propellant rocket motor that utilizes nitrogen tetroxide and the 50-50 hydrazine mixture. Test results and specimen evaluations from test series 4 indicated that the Aeronutronic solid propellant simulator exhaust environment provided the specified exhaust environment with the required.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1966
- Accession Number
- AD0804607
Entities
People
- C. S. Mayo
- H. Blaes
- J. L. Shaw
- S. L. Ostrow