FIELD: launch structures for space launch vehicles.
SUBSTANCE: proposed system includes rigid spatial cascade consisting of several sections shifted horizontally relative to vertical axis of symmetry. Mounted on upper points of cascade are multi-blade helicopter variable-pitch rotors with high-voltage electromechanical drive. Mounted on common axle are non-multi-blade rotors with jet drive; air propellers at varying direction of thrust are mounted over perimeter of cascade; they are also provided with electromechanical drive. Secured at edge of axis of symmetry of cascade (on separately flying cascade with main rotors) are high-voltage wires ; noise-protective control cabin is mounted on opposite edge. Secured to lower points of cascade are slings whose lower ends are connected to space rocket holding device; these slings are separable.
EFFECT: enhanced reliability of heavy and superheavy space rockets at rated altitude in troposphere.
4 cl, 12 dwg
