An investigation of the acceleration induced burning rate increase of nonmetallized composite propellants

A model is developed which correlates the experimentally observed burning rates of composite nonmetallized propellants subjected to acceleration fields normal to the burning surface. The model attributes the increased burning rates to additional energy transfer to the propellant surface from the combustion of ammonium perchlorate particles retained on the propellant surface by the acceleration forces. A method for predicting, with limited experimental data, the burning rate of a propellant as a function of pressure and acceleration is described.