Development and Evaluation of an Ablative Closeout Material for Solid Rocket Booster Thermal Protection System.

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)

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1979
Accession Number
ADA305668

Entities

People

  • W. J. Patterson

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Amines
  • Booster Rocket Engines
  • Chemistry
  • Engineering
  • Environment
  • Epoxy Resins
  • Failure Mode And Effect Analysis
  • Flight
  • Materials
  • Mechanical Properties
  • Rockets
  • Space Flight
  • Tensile Strength
  • Test And Evaluation
  • Test Facilities
  • Thermal Properties
  • Wind Tunnels

Readers

  • Aerospace Engineering.
  • Robotics and Automation.
  • Rocket Propulsion.

Technology Areas

  • Space
  • Space - Hall-Effect Thruster