The cohesive law of particle/binder interfaces in solid propellants

Abstract

Solid propellants are treated as composites with high volume fraction of particles embedded in the polymeric binder. A micromechanics model is developed to establish the link between the microscopic behavior of particle/binder interfaces and the macroscopic constitutive information. This model is then used to determine the tension/shearing coupled interface cohesive law of a redesigned solid rocket motor propellant, based on the experimental data of the stress strain and dilatation strain curves for the material under slow rate uniaxial tension.

The effect of interface shock viscosity on the strain rate induced temperature rise in an energetic material analyzed using the cohesive finite element method

“…CFEM has been used extensively for simulating the impact induced damage behavior of different composite materials [34][35][36][37][38][39][40], including energetic materials [22][23][24]41]. CFEM application to a material with unknown crack path can be approached in two ways; the first is to dynamically insert cohesive surfaces into the model as fracture develops and the second is to define all bulk element boundaries as cohesive surfaces.…”

“…This technique can be implemented to model fracture in individual components as well as the interface separation behavior of the microstructure. Cohesive zone models (CZMs) have been used by many researchers [22][23][24][25] to simulate the interface debonding. Barua et al [22,23,26,27] have studied the microstructural level response of various idealized PBXs under shock induced impact loading using CZM.…”