STUDIES RELATED TO THERMOVISCOELASTIC STRESS ANALYSIS OF HIGHLY-LOADED SOLID PROPELLANT.
Final technical rept. 1 Dec 65-30 Sep 66,
PURDUE UNIV LAFAYETTE IND SCHOOL OF AERONAUTICS ASTRONAUTICS AND ENGINEERING SCIENCES
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The report covers studies which account for realistic solid propellant properties, including nonlinear viscoelastic behavior, in the structural analysis of idealized configurations under slow cooling and ignition pressurization. First, approximate linear viscoelasticity solutions are given which illustrate certain essential features of propellant structural response, and demonstrate the applicability of quasi-elastic solutions. Specific nonlinear constitutive equations, for both mechanically compressible and incompressible materials, are then derived from a thermodynamic theory. An experimental program and data reduction scheme for evaluation of material properties is discussed. Application of nonlinear theory is made to long, hollow, case-bonded cylinders using actual propellant properties, and linear and nonlinear solutions are compared numerically. Author
- Solid Rocket Propellants