An Investigation of Polymer Nanocomposite Ablatives Characterization

摘要

Nanostructured ablatives have been prepared by blending two types of polymer systems with three types of nanoparticles. TGA and SEM analyses were used to characterize these materials under laboratory and scaled solid rocket motor heating conditions. Kevlar-filled ethylene-propylene-diene rubber (EPDM) is used as motor insulation and carbon phenolic composite is used as nozzle assembly ablative in solid rocket propulsion systems. Five phenolicanoparticle blends consisting of 30 wt% carbon black, 15 wt% POSS, 5 wt% nanoclay, 10 wt% nanoclay, and 15 wt% nanoclay were selected. EPDM blends consisting of Kevlar fibers and carbon nanofibers are also included in this study. Results of various TGA tests at different heating rates will be presented. SEM analyses of virgin and charred samples will be shown. TGA and scaled solid rocket motor samples will be compared.