FIELD: rocketry and space engineering; injection of civil and military spacecraft into near-earth orbits. SUBSTANCE: stage is made in form of single unit in form of smooth-wall tube which is mounted on pylons coaxially relative to central unit of second stage of launch vehicle for separation from it. Combustion chambers of main jet engines of first stage are located over perimeter of tail section of tube. Afterburning chamber which may be provided with Laval nozzle is mounted on the outside of these chambers. Propellant and oxidizer tanks are located in tubular wall of first-stage unit and nose section of this stage in made in form of circular cone. Stabilizers with control chambers on their fences are mounted on outer surface of tube. EFFECT: increased thrust-to- weight ratio of first stage of launch vehicle; reduction of time required for injection of spacecraft into orbit. 2 cl, 6 dwg
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