SMALL-PULSE IMPULSE RPRE WORKING IN THE LOW-SPEED DETONATION MODE Russian patent published in 2018 - IPC F02K9/00 F42B10/00 

FIELD: engines and pumps.

SUBSTANCE: invention relates to the design of small-sized pulsed solid-propellant rocket engines (RPREs), which are widely used as means for correcting the trajectory of flight of guided missiles, projectiles and spacecraft. Invention proposes small-size pulsed engines of extremely simple design, consisting of a cylindrical combustion chamber and a divergent nozzle. As a fuel, mixtures based on PCA, molded as cylindrical blocks without a channel by pressing or casting, and having a porosity of several percent, are used. Combustion of fuel is carried out in the low-velocity detonation mode, which is excited by a compressed hexogen pallet placed at the end of the fuel rod and ignited by an electric igniter. This allows to obtain engines with an extremely short operating time of less than 2 ms, with a high specific impulse of up to 260 s, giving a total pulse in the range of 80–1,000 N·s. Short running time ensures maximum speed, which introduces minimal errors in the correction maneuvering of missile and projectile.

EFFECT: extreme simplicity of design, extremely low heat losses, rapid ignition of fuel in the front of a low-velocity detonation wave and combustion throughout the entire volume makes the new type of engines reliable and trouble-free, with a minimum variation in the specific impulse; simplicity of design also ensures ease and economy of production along with high quality.

1 cl, 2 dwg