MULTISTAGE CARRIER ROCKET Russian patent published in 2009 - IPC B64G1/22 

FIELD: transport; astronautics.

SUBSTANCE: carrier rocket consists of four side, central and terminal units forming its first, second, and third stages, control system, systems securing ground-based information and telemetery control. Each unit is supplied with engine for pumping fuel components, fuel tanks, pressurisation systems for actuating gas/fluid in intake and storage fuel tanks made as sphere-balloons, feeding fittings for filling-in uncooled actuating gas/fluid, sensors and instrumentation. Pressurisation system of third stage fuel tanks is made as single-main distribution. Actuating gas/fluid for tank pressurisation is gaseous substance with evaporating temperature below that of oxidant. Volume of sphere-balloons is less than volume occupied by preset quantity of actuating gas/fluid at temperature equal to oxidant temperature and pressure not exceeding admissible one for retaining soundness of sphere-balloons. Temperature of actuating gas/fluid at feeding fittings inlet is considerably higher than that of oxidant. Inlet of each sphere-balloon is pneumatically connected with docking device of feeding fittings located at joint between central block and third stage. Pneumatic main of pressurisation system of said tanks is connected with engine heat exchanger. Pressure gauges measuring pressure of actuating gas/fluid in sphere-balloons are functionally related to system securing ground-based information and telemetery control.

EFFECT: launching of relatively big payload to orbit.

2 dwg