CREATION METHOD OF AERODYNAMIC NOZZLE OF MULTICHAMBER PROPULSION SYSTEM, AND NOZZLE UNIT ASSEMBLY FOR METHOD'S IMPLEMENTATION Russian patent published in 2014 - IPC F02K9/97 

FIELD: engines and pumps.

SUBSTANCE: at creation of a nozzle of a propulsion system there created is an outside flow of gases from primary nozzles of a multichamber propulsion system with a central body at the first stage of a carrier rocket and an inside flow of gases from primary nozzles of liquid-propellant engines made as per a closed scheme with afterburning of a gas-generator gas of the multichamber propulsion system of the second stage of the carrier rocket with a single disc-type nozzle. Disc-type nozzle symmetry axis coincides with central body symmetry axis. A lower edge of the single disc-type nozzle of the propulsion system of the second stage of the carrier rocket is aligned with the lower edge of the central body of the multichamber propulsion system of the first stage of the carrier rocket. Another invention of the group relates to the nozzle unit assembly of the multichamber propulsion system, which includes primary nozzles and a central body in a shank part of the first stage of the carrier rocket and primary nozzles of the multichamber propulsion system of the second stage of the carrier rocket with the single disc-type nozzle. The single disc-type nozzle of the propulsion system of the second stage of the carrier rocket is put into the inner cavity of the central body. Disc-type nozzle symmetry axis coincides with central body symmetry axis. The lower edge of the single disc-type nozzle of the propulsion system of the second stage of the carrier rocket is aligned with the lower edge of the central body of the multichamber propulsion system of the first carrier rocket stage.

EFFECT: group of inventions allows increasing a specific impulse of a propulsion system.

6 cl, 17 dwg