Nondestructive Evaluation of Rocket Motors; Finite Element Analysis of Solid Propellant Failure

摘要

A linear elastic finite element model of the Shrike missile was developed and run in a series of parametric studies to determine the effect of a cookoff-induced gas bubble upon the missile case and propellant. A series of case-to-liner interface. The model identified the critical gas bubble pressures to rupture the case or propellant, and evaluated the peel tests for their worthiness in the cookoff situation.