SOLID PROPELLANT ROCKET ENGINE Russian patent published in 2023 - IPC F02K9/95 F02K9/97 

FIELD: rocket technology.

SUBSTANCE: rocket engine comprising a housing, a combustion chamber, a nozzle, an exit cone, a solid propellant charge, an igniter, a bushing and a stopper with a fixed stall force; according to the invention, an annular support with a stopper of a given profile is mounted at the beginning of the exit cone, while the front end of the stopper is made under angle α =(1-9°) to the cross section of the rocket engine, and the support is made of a composite material, for example, fiberglass, and the shear stress of the stopper material is lower than the shear stress of the sleeve material, in particular cases made of metal, and in the area L=(0.0006 to 0.005) d⋅P_m supports formed by a number of stoppers, where d is the diameter of the sleeve facing the critical section of the nozzle; P_m is the maximum pressure in the combustion chamber; L is the length of the support section, on which a number of stoppers is located; α is the angle of inclination of the support stopper.

EFFECT: increased reliability of the structure in the process of starting operation by reducing the likelihood of violation of the integrity of the output cone by fragments of the igniter attachment.

3 cl, 3 dwg