FIELD: transport.
SUBSTANCE: invention relates to rocketry, particularly, to multistage carrier rocket assembly. Proposed rocket comprises first stage central module with first stage lateral modules and second stage central module with second stage lateral modules. All modules are equipped with liquid-propellant rocket engine and system to transfer fuel components from lateral modules into central module. Carrier rocket comprises bank nozzle units with two opposed bank nozzles fitted on outer surface of lateral modules of all stages remote from carrier rocket axis. Liquid-propellant rocket engine comprises bearing frame, combustion chamber suspended thereto and provided with cylindrical part with top and bottom structural rings, and nozzle. Suspension assembly is mounted on bearing frame and includes moving and stationary parts. Said moving part is connected via intermediate frame with top structural ring. Bank nozzles are arranged on bottom structural ring mounted at nozzle bottom and coupled with nozzle edge. Producer-gas feed pipelines are connected via three-way gas and fuel valves to bank nozzles, their opposite ends being connected to gas bleed pipeline. Fuel pipelines are also connected to bank nozzles secured at carrier rocket bottom structural ring. Turbo pump unit comprises turbine and oxidiser pumps, two-stage fuel pump and extra fuel pump with their shafts coupled by torque transfer and rpm control device arranged in housing with feed and discharge ducts. Torque transfer and rpm control device is made up of magnetic transmission incorporating disc with permanent magnets regularly spaced in circle.
EFFECT: better controllability.
11 cl, 19 dwg
