Thermal analysis of viscoelastic propellant grains with developed axisymmetric finite elements using herrmann formulation

Nitesh Kumar

Research output: Contribution to journalArticle

Abstract

Solid Rocket Motor (SRM) is developed based on casting method where solid propellant grains are cast into a composite or metallic casing. Generally, SRMs are exposed to extreme loading scenarios during storage, transportation, and firing, leading to cracks in the solid propellants. In this paper, Computational Finite Element Analysis is performed with developed 8 node quadrilateral, 9 node quadrilateral and 6 node triangular elements using Herrmann formulation to analyze stress and strain variations in the head and mid segments of the SRM subjected to thermal loading. The obtained results are compared with commercially available Finite element software.

Original languageEnglish
Article numberIJMPERDDEC201878
Pages (from-to)773-782
Number of pages10
JournalInternational Journal of Mechanical and Production Engineering Research and Development
Volume8
Issue number6
DOIs
Publication statusPublished - 14-12-2018

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Solid propellants
Rocket engines
Propellants
Thermoanalysis
Casting
Cracks
Finite element method
Composite materials
Hot Temperature

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Mechanical Engineering
  • Fluid Flow and Transfer Processes

Cite this

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