In this paper, a novel pyrogenic pulser was designed both analytically and numerically and was evaluated with empirical tests. The motivation of this study was the need for active control of the aero acoustic pressure oscillations by injecting the secondary flow into the solid rocket motor. First, in brief, pyrotechnic and pyrogenic pulsers were introduced, and then analytical goving equations were presented in three transient, sinusoidal and Hercules methods. In order to under-stand the intal pressure of the pulsar and its plume length, the injection flow field was evaluated using the ANSYS-Fluent software with both k-ωSST and k-εRealizable models both at ambi-ent and motor pressure. After that, the design and manufacturing of the pulser hardware and the test process were described. Finally, analytical, numerical and experimental results were discussed. The results show that there is a good correlation between the transient analysis in theory and the numerical solution by the k-ωSST model and the empirical test data. In addition, pyrogenic pul-sers design depends on various parameters of motor and pulser charge performance prediction. The quality of pulser charge bonding to its insulator and erosion of its throat path due to injection have an important role to obtain a desirable pulser mass flow rate and plume length.