Accession Number : AD0813410

Title :   A NEW TECHNIQUE FOR MECHANICAL STRENGTH TESTING OF RAPIDLY CHARRED ABLATION MATERIALS.

Descriptive Note : Rept. for Dec 65-Dec 66,

Corporate Author : AEROSPACE CORP EL SEGUNDO CA LABS DIV

Personal Author(s) : Welsh, William E., Jr. ; Ching, Alfred

Report Date : FEB 1967

Pagination or Media Count : 19

Abstract : Mechanical strength of rocket nozzle liner or reentry vehicle ablation materials is of increasing interest in cases where mechanical loss may comprise a major loss or failure mechanism during rocket firing or reentry. Previous studies of reinforced plastics have utilized specimens heated and charred slowly prior to the application of load. Since heating is rapid during rocket firing or reentry, it appeared to interest to develop a new technique for heating and loading in time periods typical of these two stages, on the order of 10 seconds. Such a technique was developed, utilizing a high temperature plasma arc flow to heat slender specimens and pneumatically actuated loading frame to apply stress. Initial results were obtained for tensile strength in the laminate direction of phenolic graphite and phenolic carbon materials, and interlaminar shear strength of phenolic graphite. The technique appears promising for determination of strength in various loading-laminate orientations, elongations, and moduli, and for studies of heating rate effects on strength. (Author-PL)

Descriptors :   (*ABLATION, PLASMA JETS), (*PHENOLIC PLASTICS, GRAPHITE), (*REFRACTORY MATERIALS, TENSILE PROPERTIES), THERMAL SHOCK, SIMULATORS, CARBON, ELECTRIC ARCS, TEST METHODS, LAMINATED PLASTICS, TEXTILES, IMPREGNATION.

Subject Categories : Laminates and Composite Materials

Distribution Statement : APPROVED FOR PUBLIC RELEASE