1. The rocket-space complex consists of a transport-launch container and a multistage launch vehicle with a space rocket module with a main fairing; the space rocket module is made in the form of the main compartment of the last stage of the launch vehicle; the launch vehicle is equipped with liquid engines, and its main compartment is mounted on a platform with a hydraulic position control unit, fed from the fuel supply line to the liquid engine of the last stage of the launch vehicle; the launch vehicle also contains at least one tank of liquid fuel components in each stage, each tank containing a separate membrane of liquid and gas cavities of high pressure, the main fairing of the launch vehicle contains aerodynamic rudders, and the transport container contains water in the sub-missile compartment.

2. The flight of the launch vehicle of the rocket-space complex is controlled by changing the position of the center of mass relative to the thrust vector of the engines of each stage of the launch vehicle, namely the deviation of the main compartment of the last stage of the launch vehicle relative to the thrust vector of each stage of the launch vehicle.

3. The method of flight control specified in item 2 is innovative, after all deviation of the main compartment of the last stage of the launch vehicle is carried out by reciprocating movement of rods of hydraulic drives.

4. The control methods specified in paragraphs 2 or 3 are innovative in that the pressure of the steam generated in the launch vehicle gives the launch vehicle a translational motion at a speed sufficient for the launch vehicle to fly in the atmosphere for aerodynamic control.

5. The method according to any one of paragraphs 2-4, is innovative in that the temperature in the combustion chamber of at least one engine is reduced by using hydrogen peroxide and ethanol as components of rocket fuel, in their stoichiometric ratio, where each component is in an aqueous solution of 98-100% concentration .

6. The method according to any one of paragraphs. 2-5, is innovative in that high-pressure gas from the fuel tanks is used to brake and control the return flight of the stages of the launch vehicle.

UA123891.pdf