Development of a Solid Rocket Propellant Nonlinear Constitutive Theory
Final rept. May 1973-Jul 1974
AEROJET SOLID PROPULSION CO SACRAMENTO CA
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The objective of this program was to develop and demonstrate the accuracy of totally computerized response and failure characterizations and finite element stress and deformation analyses of propellant systems. These analyses were to be based on the nonlinear viscoelastic constitutive theory developed on earlier Air Force and Navy contracts. To meet these objectives, the work to be accomplished was divided into four distinct tasks. Tasks I and III were development tasks wherein the computerized characterization and finite element programs were defined, coded and assembled. Tasks II and IV were demonstration tasks wherein the developments of Tasks I and III were evaluated in realistic situations. The technical discussion of this report provides a detailed description of the work performed to meet the objectives of this program. Also included under separate headings are the descriptions of each computer code, its function, and sample problems.
- Solid Rocket Propellants