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

Abstract

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. Keywords: Nondestructive evaluation, Cookoff, Finite element analysis, Shrike, Peel test.

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Document Details

Document Type
Technical Report
Publication Date
Jul 31, 1986
Accession Number
ADA192890

Entities

People

  • Charles E. Anderson Jr.
  • P. A. Cox
  • Scott A. Mullin

Organizations

  • Southwest Research Institute

Tags

DTIC Thesaurus Topics

  • Classification
  • Crack Tips
  • Failure Mode And Effect Analysis
  • Finite Element Analysis
  • Geometry
  • High Temperature
  • Materials
  • Propellants
  • Radial Stress
  • Rocket Engines
  • Rocket Models
  • Rocket Propellants
  • Rockets
  • Solid Propellants
  • Stress Intensity Factors
  • Test And Evaluation
  • Two Dimensional

Readers

  • Aerospace Test and Evaluation
  • Rocket Propulsion.
  • Structural Health Monitoring of Composite Structures.