ABSTRACT
Fuel-rich propellant compositions, used in air-augmented rocket propulsion, contain a high-energy fuel component in the form of finely divided boron, wherein boron is present in large excess of the amount oxidizable during the combustion of the propellant. The burning of fuel-rich propellant is a process in which the solid phase becomes gaseous products of high temperature through decomposition, burning, and reaction. The burning rate temperature sensitivity of solid propellant indicates the influence of change of initial temperature of the propellant on the burning rate or the pressure inside the combustion chamber. The burning rate of propellant could be measured by a kind of Target Line Method. With fluorinated compound such as PTFE, the intensive oxidation between boron and fluorine would heat boron particles and increase the propellant burning rate. In general, agglomerated boron would be applied inside boron-based fuel-rich propellant to improve the burning rate of propellant.
