Accession Number : ADA307038
Title : Performance of Three Ablation Materials During Simulation of Long-Duration Afterbody Heating.
Descriptive Note : Technical memo.,
Corporate Author : NATIONAL AERONAUTICS AND SPACE ADMINISTRATION HAMPTON VA LANGLEY RESEARCH CEN TER
Personal Author(s) : Dow, Marvin B. ; Tompkins, Stephen S.
PDF Url : ADA307038
Report Date : JAN 1967
Pagination or Media Count : 36
Abstract : An experimental investigation was made to determine the resistance to heat penetration and deformations or buckling of three ablation materials during simulated exposure to lifting vehicle afterbody heating conditions. The ablation materials, which were bonded to inconel cones, were subjected to convective heating at cold-wall heating rates ranging from 4 to 40 Btu/sq ft-sec (45 to 454 kW/sq m) in arc jet streams of air and nitrogen. The ablation materials tested were a molded epoxy-based composite and a silicone elastomeric with and without honeycomb reinforcement. For the test conditions of the investigation, models with the epoxy-based composite and the unreinforced silicone elastomeric developed buckles in the ablation material; two models of the epoxy-based composite failed catastrophically. The honeycomb reinforcement in the silicone elastomeric was beneficial in restraining thermal expansion and maintaining char integrity. Except for tests in nitrogen, the silicone elastomerics provided the best resistance to heat penetration.
Descriptors : *REENTRY VEHICLES, *SPACECRAFT, *ELASTOMERS, *EPOXY COMPOSITES, *PLASTICS, DEFORMATION, NITROGEN, THERMAL EXPANSION, BONDED JOINTS, BUCKLING, ARC JET ENGINES, HEAT SHIELDS, CONVECTION(HEAT TRANSFER), FAILURE(MECHANICS), EPOXY RESINS, ENTHALPY, CONICAL BODIES, NOSE CAPS, HEAT RESISTANT MATERIALS, HONEYCOMB STRUCTURES, ABLATIVE MATERIALS, NICKEL ALLOY INCONEL, CHARRING, AFTERBODIES.
Subject Categories : Laminates and Composite Materials
Elastomers and Rubber
Distribution Statement : APPROVED FOR PUBLIC RELEASE