Zenit-3SLБ space purpose rocket developed under the Land Launch program for spacecrafts’ launches from Baikonur Cosmodrome to low, middle and high near-earth orbits (including transmitting to geostationary and geostationary), as well as to definite trajectories.
Technical characteristics Value
Maximum launching mass, tone 473
Payload mass, placing into transmitting orbit, tone determinig before launch
Fuel and oxidizer mass, tone 425
Engine thrust during the start, ton-force 740
Maximum overload during start, units 4,0
Propellant components kerosene/liquid oxygen
Total length, meter 58,7
Diameter I and II stages, meter 3,9
Upper-stage rocket block diameter, meter 3,7
Main fairing diameter, meter  4,10
Stages quantity3