ROCKET ENGINE FOR SOLID FUEL FOR HINDER PARTS SEPARATED Russian patent published in 2019 - IPC F02K9/32 F02K9/30 F02K9/95 

FIELD: engines and pumps, rocket engineering.

SUBSTANCE: rocket engine of solid fuel for removal of detachable parts of the rocket consists of a body with a solid multi-charge located between the support grids and two gas-bound nozzles. In the pre-cool volumes of the housing, coaxially with the gas supply tube with a pyro cartridge, the igniters are fixed, each of which contains a perforated cup with a case installed inside, filled with pyrotechnic composition. Glass on the side of the gas inlet tube is closed with a lid with an annular conical reflector. Between the wall of the reflector and the end of the case in the side wall of the cover there is a circular row of through channels connecting the internal cavity with the pre-nozzle volume. Outer diameter of the annular conical reflector d_ref is 0.4…0.5 of the internal diameter of the shell (d_ref=(0.4…0.5)D_sh). In the wall of the reflector on the diameter d_row, equal to 0.6…0.8 from the outer diameter of the conical reflector (d_row=(0.6…0.8)d_ref), additionally made a number of through holes, the axes of which are perpendicular to the outer side of the reflector. In the frontal section, the axes of the holes in the reflector are offset relative to the axes of the through channels of the lid and are located in the sector between them, and the diameter of the circular row of holes in the reflector is larger than the diameter of the circular row of holes in the lid. In the reflector can be made more than one row of holes.

EFFECT: invention will reduce the influence of the pressure waves of the products of charge combustion by reducing the amplitude of the pressure waves.

1 cl, 4 dwg