STAROVEROV'S CONICAL ROCKET ENGINE 8 (VERSIONS) AND METHOD OF ITS VERTICAL LAUNCHING (VERSIONS) Russian patent published in 2014 - IPC F02K9/08 F02K99/00 

FIELD: engines and pumps.

SUBSTANCE: proposed engine comprises solid-propellant grain with one or several channels extending over the entire grain length filled with propellant of quicker ignition than that of the primary propellant. Or, said grain has several parallel channels. Note here that some of them tear off the grain surface at distance equal to or larger than that between adjacent channels. In case several channels are made in said grain, these are located in parallel or in direction towards cone vertex. In compliance with another version, inclined channels are inclined over the grain entire length or in its rear part periphery. Note here that ignition rate of leader-propellant, or leader-propellant and primary propellant decrease. Engine rear has central conical recess with several recesses with their leader-propellant charges that tear off the preset distance from engine rear end. Besides, several parallel or converging channels can be made at engine front and filled with higher ignition rate than that of the primary propellant. Note here that ratio between length of separate peripheral channel and ignition rate are selected to make ignition rate of all propellants in all channels equal. This makes the engine gas capacity per unit area constant. In compliance with the other versions, engine front lateral part is composed of one or several conical layers and by primary propellant with higher ignition rate while of premade conical recess at engine rear end occupies the part of rear end surface. Besides, primary propellant ignition rate can decrease either continuously or by layers at periphery. At vertical start of conical rocket engine it is mounted at horizontal surface with resilient coating and hole at the centre. Prior to starting, engine is retained in vertical position by elastic suckers arranged over its outer surface.

EFFECT: no need in engine division into stages, variable thrust.

20 cl, 2 dwg