Laser technique for determining solid propellant transient burning rates during oscillatory combustion

The laser technique was developed for measurement of transient burning rates of solid propellant during oscillatory combustion. the design and operation of the system are discussed. A high pressure window bomb was used for the combustion chamber. A modulating disk was used to induce the pressure oscillation above the combustion bomb. The oscillatory frequency was controlled easily with selecting the rotating velocity of the disk. Test results with AP/PS propellants, were in agreement with the results of previous techniques.