| 摘要 |
FIELD: transport space systems. ^ SUBSTANCE: proposed launch vehicle has two-stage cluster in form of central second-stage module and four side first-stage modules of taper configuration. Side modules are mounted in plane of stabilization of launch vehicle at angle relative to axis of central module. Third stage and payload are located in succession with first and second stages. Modules are provided with propellant component tanks, cruising and control liquid propellant rocket engines, as well as load-bearing units with spherical supports in upper part of side first-stage modules, upper load-bearing strake on central second-stage module and load-bearing coupling members of cluster tail section. Central module is cylindrical in area of location of oxidizer tank and has shape of truncated cone changing to cylinder in area of location of fuel tank. Central module surface is provided with grooves for lateral taper surfaces of side first-stage modules; these lateral surfaces are located at clearance relative to grooves. Diameter of launch vehicle depends on position of side modules relative to longitudinal axis of central module similarly to known launch vehicles, such as P-7A. ^ EFFECT: increased mass of payload at retained transversal diameter of launch vehicle; reduced expenses for development of launching complex. ^ 5 dwg |
