SOLID-PROPELLANT ROCKET ENGINE Russian patent published in 2012 - IPC F02K9/18 

FIELD: engines and pumps.

SUBSTANCE: solid-propellant rocket engine includes channel charge rigidly attached to internal walls of housing by means of protective strengthening layer, housing with front and nozzle bottoms, nozzle and ignition assembly. Axial charge channel is made of conical section of round cross section convergent towards the nozzle and conical section of star-shaped cross section. Minimum diameter of conical section of channel charge is 0.8…0.9 of maximum diameter of axial channel. Depth of grooves of star-shaped section of channel is increased linearly towards rear face of charge and is 0.65…0.85 (on rear face) of burning charge arch on the front face of charge. Opening angle of beams of star-shaped section of channel is 15…20°. Tops of projections in the channel between beams form conditional cylindrical surface the diameter of which equals to minimum diameter of conical section of the channel. Length of start-shaped section of the channel is 0.20…0.25 of charge length.

EFFECT: invention allows increasing volumetric filling of the housing with fuel, obtaining neutral pressure-time diagram, eliminating degressive fuel residue, reducing heat and gas dynamic losses, improving combustion completeness of metal fuel particles, as well as decreasing the spread in power and intraballistic characteristics.

4 dwg