Abstract
This paper reviews several methods used by the author in the stress analysis of rocket propellantgrain models with different boundary conditions, subjected to different loading conditions. The objective of the analysis is to help the designer to develop a stress-wise better grain configuration. Some assumptions have to be introduced to attain this goal in a practical way since some propellants behave nonlinearly, nonelastically, and are heterogeneous and anisotropic. Several indices are presented to evaluate designs. The method used by the author to “optimize” designs is also presented.
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