HYBRID ROCKET ENGINE Russian patent published in 2014 - IPC F02K9/72 

FIELD: engines and pumps.

SUBSTANCE: hybrid rocket engine involves a charging chamber with a solid fuel component charge located in it, along which axis made is a through channel, an injector head of combustion chamber, an afterburner, a tank with liquid fuel component, a system of discrete measurement of solid and liquid fuel components levels, the main feed line with redistribution unit of supplied fuel component, parameters control elements. The afterburner is made after solid fuel component charge, which channel is connected to the afterburner cavity. The injector head consists of cylindrical injector head and afterburner injector head of cylindrical or lenticular form. The cylindrical injector head contains two independent coaxial channels connected to redistribution unit of fuel component supplied to combustion chamber. External channel of cylindrical injector head is connected to injectors located in cylindrical injector head in solid fuel channel. Internal channel of cylindrical injector head is connected to injectors of cylindrical or lenticular form injector heads of the afterburner located as an extension of cylindrical injector head and located in the afterburner cavity.

EFFECT: increasing factor of chamber filling with fuel, reducing dimensions and structural mass of rocket engine and improving its reliability.

5 dwg