SOLID-PROPELLANT ROCKET ENGINE Russian patent published in 2024 - IPC F02K9/95 F02K9/96 

FIELD: rocketry.

SUBSTANCE: invention relates to rocketry and is intended for use in jet projectiles. Rocket engine, comprising a housing, a bottom, a solid propellant charge, a nozzle and an insert in its outlet cone, an ignition unit and a nozzle plug, feature consists in the fact that ignition unit is equipped with afterburner tube, length of which and distance from outer surface of afterburner tube to insert, respectively, is (1.02…4.5) and (0.02…0.66) of the insert diameter in the plane passing through the afterburner tube end, wherein afterburner tube is rigidly secured to nozzle plug. In particular cases, nozzle plug is made from composite material, for example from fiberglass, wherein the shear stress of the nozzle plug material is lower than the shear stress of the nozzle material, and on section L₁=(0.00015…0.0012) d_a⋅P_m plugs forcing elements are made, where d_a is the diameter of the outer surface of the outlet section of the nozzle; P_m is maximum pressure in combustion chamber; L₁ is the width of the section of the nozzle plug, on which the forcing elements are located.

EFFECT: invention improves the reliability of the design during the process of reaching the operating mode by reducing the likelihood of damage to the integrity of the output cone by fragments of the ignition device.

3 cl, 2 dwg