| 摘要 |
FIELD: space engineering; transport space systems provided with engine plants working on oxygen-hydrogen propellant. SUBSTANCE: nonexpendable vertical takeoff and landing launch vehicle at tandem attachment of payload includes liquid-propellant rocket engine with central body and module combustion chambers, central auxiliary spherical tank with taper upper portion and attachment units, side taper integral tanks with cable locking system and load-bearing units for attachment of payload. Module combustion chambers of liquidpropellant rocket engine are located on the outside of taper lower part of circular load-bearing frame inside fairings mounted at spaced relation to each other. Side taper integral tanks are smoothly distributed in radial plane of launch vehicle at inclination relative to its axis and are articulated over periphery of circular load-bearing frame. Side tanks are interconnected in upper part by means of detachable coupling units. Invention provides for enhanced efficiency of launch vehicle due to increased mass of payload and service life of vehicle due to avoidance of intermediate frame of payload attachment. EFFECT: enhanced efficiency and reliability. 6 cl, 8 dwg |
