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.
Nondestructive Evaluation of Rocket Motors; Finite Element Analysis of Solid Propellant Failure
1986
100 pages
Report
No indication
English
Rocket Propellants , Jet & Gas Turbine Engines , Finite element analysis , Nondestructive testing , Solid propellant rocket engines , Failure(Mechanics) , Solid rocket propellants , Bubbles , Cook off , Failure , Gases , Guided missiles , Peel strength , Pressure , Rupture , Rocket engine cases , Combustion chamber liners , Internal pressure , Air to surface missiles , Shrike missile
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