Abstract: The invention relates to a space-rocket technology an can be used for both a pilot-controlled and unpiloted space craft in the earth's orbit. The inventive method consists in igniting-up cruising liquid-fuel rocket engines (LRE) of all assembly units, when the propulsion power of LRE of the side units is set to maximum and the LRE of the central unit is set relatively low.

Abstract: The invention relates to a space-rocket technology and can be used for placing both a pilot-controlled and unpiloted space craft in the earth's orbit. The inventive method consists in igniting-up cruising liquid-fuel rocket engines (LRE) of all assembly units, when the propulsion power of LRE of the side units is set to maximum and the LRE of the central unit is set relatively low.

Abstract: The invention relates to a space-rocket technology and can be used for placing both a pilot-controlled and unpiloted space craft in the earth's orbit. The inventive method consists in igniting-up cruising liquid-fuel rocket engines (LRE) of all assembly units, when the propulsion power of LRE of the side units is set to maximum and the LRE of the central unit is set relatively low.

Abstract: The invention relates to the field of rocket-space engineering and may find application during the development of rocket-space systems serving to place manned and unmanned space ships into a near-earth orbit.

Abstract: The invention relates to the field of rocket-space engineering and may find application during the development of rocket-space systems serving to place manned and unmanned space ships into a near-earth orbit.

Abstract: A booster comprises a body including tanks for an oxidizer and fuel, a nose compartment with a dome, a between-tank section and an afterbody, a rocket engine installation, an all-moving wing with a unit for turning it and fixing in a position along the axis of the booster during the ascension step and in a position turned by 90° during the return flight, horizontal and vertical fin assemblies, a triple-point support landing gear, aerodynamic control organs and units for jointing to the second stage of the launch vehicle. The booster is provided with an air-feed jet engine installation, comprising two engines with air intakes mounted in the nose compartment, and with gas-line extensions with exhaust nozzles extending beyond the bypasses of the external contours of the nose compartment, and a propellant system with propellant tanks in the wing, working and balancing tanks in the nose compartment. A wing is mounted on the upper surface of the booster body in the area of the between-tank section.

Abstract: The invention relates to the field of rocket-space engineering and may find application during the development of rocket-space systems serving to place manned and unmanned space ships into a near-earth orbit.