Accession Number : ADA307843
Title : Experimental Evaluation of Several Advanced Ablative Materials as Nozzle Sections of a Storable-Propellant Rocket Engine.
Descriptive Note : Technical memo.,
Corporate Author : NATIONAL AERONAUTICS AND SPACE ADMINISTRATION CLEVELAND OH LEWIS RESEARCH CEN TER
Personal Author(s) : Pavli, A. J.
PDF Url : ADA307843
Report Date : APR 1968
Pagination or Media Count : 26
Abstract : Eighteen ablative materials were evaluated for their relative erosion resistance in test firings of 22 nozzles in a storable-propellant engine of a 1.2-inch (3.05-cm) diameter throat at a chamber pressure of 100 psia (689. 5 kN/m2). The materials investigated were the phenolic, polyimide, phenolic plus polyamide, epoxy novalac, and phenylsilane resins, reinforced with silica, quartz, and carbon-silica fibers. Quartz reinforcement was superior to silica with the three resins tested. The lower erosion rate is attributed to the higher melting temperature of quartz. Carbon-silica reinforcement exhibited the highest erosion rate. Its relatively poor performance is attributed to the rapid oxidation of the carbon. Ablatives made of phenolic resin had lower erosion rates than all other resins tested. Erosion at mixture ratios of 1.6 was greater than at mixture ratios of 2.0. Nozzle convergent entrance angle, throat radius of curvature, and source or resin supplier had no apparent effect on erosion resistance. A slight effect of fabrication technique on erosion was detected.
Descriptors : *ABLATIVE MATERIALS, *STORABLE ROCKET PROPELLANTS, TEST AND EVALUATION, RATIOS, HIGH RATE, SILICON DIOXIDE, POLYMERS, FIRING TESTS(ORDNANCE), FABRICATION, CARBON, MIXTURES, CURVATURE, QUARTZ, OXIDATION, SILANES, NOZZLES, LOW RATE, MELTING POINT, RADIUS(MEASURE), EROSION RESISTANCE, PHENOLIC PLASTICS, POLYIMIDE RESINS.
Subject Categories : Laminates and Composite Materials
Liquid Rocket Propellants
Distribution Statement : APPROVED FOR PUBLIC RELEASE