Burning Rate Dependence of Composite Propellants on Ammonium Perchlorate Particle Size

摘要

The experimental measured results show a wide variation in the burning rate with change in AP mean diameter. The restiltant trend is a typical S shaped curve which is the characteristic of AP propellants having stoichiometric oxidizer to fuel ratios or fuel rich compositions. A simplified model is developed to calculate the propellant burning rates based on the multiple flames model concept The computed burning rates are compared with the experimental results and good agreement is found.