SOLID-PROPELLANT ROCKET ENGINE (VERSIONS) Russian patent published in 2018 - IPC F02K9/95 

FIELD: engine devices and pumps.

SUBSTANCE: solid-propellant rocket engine in the first version comprises a body with a solid fuel arranged therein, a nozzle unit installed on the rear bottom of body, an igniter includes a solid fuel igniter mounted in the front and/or rear bottom of the body. The igniter is mounted in the front bottom of the body along the axis of a central channel. The igniter includes a laser connected by a cable to a power supply source and directed by the laser beam focus of given pulse shape to a layer of flammable substance which is applied to the end of the igniter, and the igniter is placed in a perforated shell and installed in a casing with radial clearance. In the igniter installed in the front bottom of the body, the casing with its one end is airtightly connected to the laser, and on its other end there is a flare, on which a deflector of radially directed ejection of flame from the igniter is installed to the surface of through solid fuel central channel. In the igniter installed in the rear bottom of the body, the casing with its one end is airtightly connected to the laser, and the other end of the casing there is a branch pipe which to which the igniter is mounted eccentrically to the central channel in the rear bottom of the body with the possibility of concentrated ejection of flame from the igniter through a prechamber to the solid fuel end. In the second version the solid-propellant rocket engine contains armouring coatings on the ends of solid fuel, and the igniter is mounted in the front bottom of the body and is a laser. The laser drives ignition of solid fuel of directed laser beam radiation focus of specified shape of pulse through the prechamber to solid fuel end, for this purpose in the armouring coating of the solid fuel end there is a local zone of ignition with the possibility for combustion transition into the solid fuel central channel. In the third version of the rocket engine the laser is mounted eccentrically in the rear bottom of the body eccentrically to the nozzle, driving ignition of solid fuel by directed laser beam radiation focus of specified shape of pulse through the prechamber into one of the cells of pyramidal shape made on the end of solid fuel, with subsequent transition of combustion over entire honeycomb pyramidal-cellular surface of solid fuel end.

EFFECT: enhancement of reliability and reduction of ignition time of solid fuel.

3 cl, 8 dwg