ROCKET PROJECTILE PULSED MICRO ENGINE Russian patent published in 2010 - IPC F02K9/08 

FIELD: engines and pumps.

SUBSTANCE: rocket projectile pulsed micro engine comprises chamber with convex bottom, cylindrical solid propellant channel charge arranged on supports fixed in chamber, gas ducts communicated with said chamber and cover with pyrocartridge and afterburning tube laid in charge channel. Chamber bottom has conical dissector with apex nearby afterburning tube edge. Charge supports represent flat rings with radial ledges arranged above ring plane, abutting on charge faces and furnished with radial cutouts. Ring outer diameters match the chamber ID. Conical filter is arranged between cover and support, said filter being made from elastic porous heat resistant material, for example metallic rubber. Filter larger base is aligned with the support, while smaller base is aligned with cover plane. Gas ducts are in cover or chamber, on filter outer side.

EFFECT: reduced thrust pulse, nozzle minimum size and different-pulse to generate small-size projectile torque.

2 cl, 2 dwg