Fundamental Studies Relating to the Mechanical Behavior of Solid Propellants, Rocket Grains and Rocket Motors

Abstract

During the past three years, the mechanical testing of solid propellants, solid rocket grains, and solid rocket motors under idealized conditions has been receiving increased attention. Today it is not uncommon to see a multitude of new techniques and analyses being investigated. One may expect to see dummy propellant prepared with glass bead filler to observe its dilatation to rupture; to ink circles, rectangular g rids at various critical areas on a grain surface, and to observe the distortion of these grids as a result of thermal cycling and/or slump; to subj e ct rectangular parallel-opipedal-shaped specimens to both torsion and biaxial tension as well as hydrostatic compression and parallel-plate tension; to apply theories of large elastic strain, and non-linear viscoelasticity; to search for an isotropic failure criterion as well as a crack propagation criterion. In short the mechanics of propellant behavior from small deformation all the way to fracture initiation and propagation has become quite sophisticated. Gradually the results of this testing and their thinking are being integrated in a logical scheme of analysis which is being passed along to the engineer and being used in predicting performance of rocket motors. This particular program will pertain to four areas: 1) The characterization of polyurethane propellant behavior out to fracture initiation in terms of large strain theory. 2) The development of a failure criterion and crack propagation criteria for said materials. 3) The generation, where possible, of macroscopic mechanical parameters in terms of molecular parameters. 4} The solution of certain stress problems, in both linear and non-linear theory, which are prerequisite to engineering applications. As such it is part of a continuing research study of structural integrity problems in solid propellant rocket motors being conducted under the general direction of Dr. M. L. Williams in the Guggenheim Aeronautical Laboratory. This preliminary report is intended as an interim working document to be circulated for the purpose of stimulating discussion.

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