Accession Number : ADA307289

Title :   Experimental Evaluation of Several 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) : Peterson, Donald A. ; Meyer, Carl L.

PDF Url : ADA307289

Report Date : APR 1966

Pagination or Media Count : 24

Abstract : Twenty-two ablative-material samples were evaluated as nozzle sections of a storable-propellant (nitrogen tetroxide and a 50-50 percent blend of unsymmetrical dimethylhydrazine with hydrazine) rocket engine to determine general trends among the material variables and to enable comparison of such trends with those observed from similar tests with a hydrogen-oxygen rocket engine reported in NASA TN D-3258. The nominal engine operating conditions for the present investigation included an oxidant-fuel ratio of 2. 0, an initial chamber pressure of 100 pounds per square inch absolute, and an initial throat diameter of 1. 2 inches. The ablative-material nozzle samples containing high-purity silica-cloth reinforcement generally had greater erosion resistance than did those containing graphite, carbon, or asbestos reinforcement. Of the high silica-cloth reinforced ablative-material samples, generally those with a phenolic or modified-phenolic resin system had greater erosion resistance than did those samples tested with other resin systems, including phenyl silane, polybenzimidazole, and epoxy novalac. Among comparable material variables, these general trends are in agreement with those reported in NASA TN D-3258.

Descriptors :   *COMPOSITE MATERIALS, *ROCKET ENGINES, *ROCKET NOZZLES, *STORABLE ROCKET PROPELLANTS, TEST AND EVALUATION, HYDRAZINES, POLYMERS, GRAPHITE, CARBON, VARIABLES, SILANES, PRESSURE, PATTERNS, OXIDIZERS, NITROGEN OXIDES, ASBESTOS, CHAMBERS, PHENOLS, EROSION RESISTANCE, ABLATIVE MATERIALS, PHENOLIC PLASTICS, TETROXIDES, POLYBENZIMIDAZOLE.

Subject Categories : Laminates and Composite Materials
      Liquid Rocket Propellants

Distribution Statement : APPROVED FOR PUBLIC RELEASE