AbstractIn this work, a correlation between propellant burning rate and strain was established. In order to investigate the effects of strain and pressure, and to measure burning rate of composite propellants, a novel apparatus was designed and prepared. Burning rates of three formula composite propellants under different pressures and strains were measured using such device. Based on the measurements, a model for the analysis on the experimental results was proposed. It was demonstrated that the model corresponded with the experimental data if the propellant samples were under tensile strain increasing from 0 to 20%. Burning rate ratio and tensile strain obeyed the quadratic relationship, burning rate increased with strain, but there was no mutation in less than 20% deformation. Furthermore, burning rate ratio of composite propellants which had low Poisson ratio increased fast as tensile strain decreased. And the less binder component of composite propellants, the burning ratio changed more significantly under a given strain state. In addition, as the exposed area increased, the burning rate ratio became larger.
A New Erosive Burning Model of Solid Propellant Based on Heat Transfer Equilibrium at Propellant Surface