FIELD: space technology.
SUBSTANCE: invention relates to space technology. The method for separating payloads (PL) from the orbital stage (OS) of the launch vehicle is based on the use of unused remnants of liquid propellant components based on their gasification, ensuring the angular position in space and stabilization. The motion of the center of mass and around the center of mass of the OS is controlled by separate discharge of gasification products from the fuel and oxidizer tanks through adjustable nozzles (holes) of the gas-reactive system. The formation of the control and stabilizing actions is carried out by changing the critical section of the nozzle (hole) for the discharge of the steam-gas mixture from the tanks to the gas distribution station in each stabilization channel.
EFFECT: elimination of the impact of the discharged steam-gas mixture from the tanks on the separating PL.
1 cl, 3 dwg
