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 | Determining before launch |
| Fuel and oxidizer mass, tone | 425 |
| Engine trust 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 quantity | 3 |
