Effect of Oxidizer Particle Size on Burning Rate and Thermal Decomposition of Composite Solid Propellants

Abstract. Studies on Thermal decomposition of ammonium perchlorate (AP)-polysty-rene (PS) propellant and burning rate of PSlAP propellant have been carried out as a function of oxidizer particle size. Therbal decomposition of AP and AP/PS propellant as a function of AP particle size shows a maximum rate around 100 micron particle size which has been explained on the basis of Mample's theory. No such maxima is observed in the case of PS/AP propellant burning rate. 1