FIELD: engines and pumps.
SUBSTANCE: invention is related to the field of rocket engineering, namely to solid propellant rocket engines, mostly to assisted takeoff and cruise engines of cruise missiles, tactical missiles, and also to multiple artillery rocket systems. Solid propellant rocket engine comprises body, nozzle block, strongly fixed charge, igniter with perforated body, filled with pyro composition in the form of lead charge and pellets. Perforation in body is arranged in the form of cells. Between lead charge and pellets there is a ring installed, which has diametral link arranged in cross section in the form of triangle and directed with one of its tops towards lead charge. Triangle base makes 0.3-0.5 of pellet diametre. Pellets are arranged around cylindrical gas supply tube, length of which makes 0.7-0.9 of pellet length.
EFFECT: invention makes it possible to provide for high reliability of rocket engine operation and simultaneous ignition of the whole surface of solid propellant charge.
4 dwg
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