Interagency Propulsion Committee
This subcommittee analyzes experimental, analytical, and statistical techniques required in the preliminary or detailed structural design of solid propellant rocket motors, gun ammunition, and their components, and in the prediction and assessment of their structural integrity and structural service life. Specific technical areas of activity include thermomechanical characterization of response and failure behavior in propellants, liners, insulation, case materials and ammunition; structural analysis and design methods for solid rocket motors and various test specimens; experimental structural analysis methods; environmental load definitions; determination of failure mechanisms for rocket motors and components; aging characterization and predictive modeling for motor materials and components; and motor and gun ammunition service life prediction and surveillance methods.
This Subcommittee is concerned with the development, application, and verification of experimental, analytical, and statistical techniques required in the preliminary or detailed structural design of solid propellant rocket motors and gun ammunition, the assessment of their structural integrity, and with the prediction of their service life based on structural or chemical aging mechanisms. Specific technical areas include: thermo-mechanical characterization of response and failure behavior in propellants, liners, insulation, and cases; structural analysis methods for solid propellant rocket motors and gun ammunition; experimental stress analysis methods and various test specimens. The subcommittee performs technical evaluation of environmental load definition; determination of failure mechanisms for rocket motors, gun ammunition, and their components; aging characterization and prognostic and diagnostic modeling of chemical aging mechanisms; to include modeling for rocket motor and gun ammunition materials and related energetic components; motor and gun ammunition service life prediction and surveillance methods.
Although the Subcommittee does not maintain primary responsibility for propulsion system interior ballistics, it is concerned with the fluid structural interaction caused by ballistic factors as theses affect propellant grain response (e.g., strain-augmented burning, crack propagation, or DDT, etc.) with the ultimate result of structural failure. Rocket nozzle thermal-structural technology not included in the Rocket Nozzle Technology Subcommittee's charter is also addressed (e.g., elastomeric joints, small low-cost motor nozzle components, phenolic igniter mount assemblies, etc.).
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Mr. David Owen, JHU-ERG, Columbia, MD