Accession Number : ADA305668
Title : Development and Evaluation of an Ablative Closeout Material for Solid Rocket Booster Thermal Protection System.
Descriptive Note : Technical memo,
Corporate Author : NATIONAL AERONAUTICS AND SPACE ADMINISTRATION HUNTSVILLE AL GEORGE C MARSHALL SPACE FLIGHT CENTER
Personal Author(s) : Patterson, W. J.
PDF Url : ADA305668
Report Date : OCT 1979
Pagination or Media Count : 49
Abstract : A trowellable closeout/repair material designated as MTA-2 (Marshall Trowellable Ablator) has been developed in-house at Marshall Space Flight Center and has been evaluated for use on the Solid Rocket Booster. This material is composed of an epoxy-polysulfide binder and is highly filled with phenolic microballoons for density control and ablative performance. The MTA-2 material has been evaluated by mechanical property testing as well as thermal testing in a wind tunnel to simulate the combined Solid Rocket Booster trajectory aeroshear and heating environments. This material is characterized by excellent thermal performance and has been used extensively on the Space Shuttle STS-1 and STS-2 flight hardware. (MM)
Descriptors : *POLYMERS, *EPOXY RESINS, *BOOSTER ROCKET ENGINES, *THERMAL STRESSES, THERMAL PROPERTIES, ABLATION, TENSILE STRENGTH, ADHESION, SUBSTRATES, STRAIN(MECHANICS), PROTECTIVE COATINGS, POLYSULFIDES, CURING, EPOXY COMPOSITES, BINDERS, FAILURE(MECHANICS), WIND TUNNELS, ACCELERATED TESTING, SOLID PROPELLANT ROCKET ENGINES, HEAT RESISTANT MATERIALS, BALLOONS, PHENOLIC PLASTICS, ROCKET TRAJECTORIES.
Subject Categories : Laminates and Composite Materials
Solid Propellant Rocket Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE