Abstract
The development of a model of a universal pyrogenic igniter is related to the possibility of using it in a number of test systems where rocket solid fuel is used as a propellant. The wide range of application of this type of igniter is due to the possibility of composing the components in different proportions depending on the desired energetic effect. On the basis of many years of experience related to the study of existing and the development of new ignition components, an initiator system was designed for a newly designed rocket fuel igniter. This system consists of an ignition subassembly that initiates the ignition process by generating a fire pulse and a subassembly that amplifies this pulse. The subject of the study was the comparison of selected performance parameters of three variants of the amplifying charge included in the fire pulse amplifying subassembly.
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