As part of the Propellants Task (Task 2.0) on the Solid Propulsion Integrity Program (SPIP), a database of material properties was generated for the Space Shuttle Redesigned Solid Rocket Motor (RSRM) PBAN-based propellant. A parallel effort on the Propellants Task was the generation of an improved constitutive theory for the PBAN propellant suitable for use in a finite element analysis (FEA) of the RSRM. The outcome of an analysis with the improved constitutive theory would be more reliable prediction of structural margins of safety. The work described in this report was performed by Materials Laboratory personnel at Thiokol Corporation/Huntsville Division under NASA contract NAS8-39619, Mod. 3. The report documents the test procedures for the refinement and verification tests for the improved Space Shuttle RSRM propellant material model, and summarizes the resulting test data. TP-H1148 propellant obtained from mix E660411 (manufactured February 1989) which had experienced ambient igloo storage in Huntsville, Alabama since January 1990, was used for these tests.
Space Shuttle Propellant Constitutive Law Verification Tests
1995
37 pages
Report
Keine Angabe
Englisch
Manned Spacecraft , Composite propellants , Double base rocket propellants , Propellant tests , Solid rocket propellants , Space shuttles , Aerospace safety , Acrylonitriles , Computer aided design , Copolymers , Data bases , Finite element method , Polybutadiene , Polybenzimidazole , Computerized simulation , Proving , Mathematical models , Propellant combustion , Propulsion system performance , Rocket engines , Spacecraft models , Spacecraft propulsion
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