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Zenit-3SL (SEA LAUNCH)
Sea Launch system with Zenit-3SL Integrated Launch Vehicle using non-toxic propellants enables commercial launches from Equator in the Pacific Ocean into a wide range of medium and high Earth orbits including geosynchronous transfer orbit, and escape trajectories.
| Title | Value |
| Type and location | Floating site at the Equator |
| Liftoff mass, tons | 468…473 |
| Number of stages | 3 |
| Payload mass, tons: | |
| - maximum | 6,1 |
| - minimum | 1,0 |
| Payload capability: | 6,100 |
| Hp=200 km, Ha=36 000 km, i= 0o, Hcir=10 000 km, i=45o | 4,200 |
| Insertion accuracy to GTO (2.3): | |
| - perigee altitude, km | ± 10 |
| - apogee altitude, km | ± 80 |
| - inclination, deg | ± 0,25 |
Zenit-3SLB (LAND LAUNCH)
The Land Launch system provides commercial services from the Baikonur Cosmodrome onboard the Zenit-3SLB launch vehicle flying on environmentally friendly propellants. The three-stage Zenit-3SLB is a modified Zenit-3SL and is capable of delivering satellites to medium and high circular and elliptical Earth orbits, including geosynchronous transfer orbit, geosynchronous orbit, and escape trajectories.
| Title | Value |
| Launch weight, tons | 463 – 466 |
| Number of stages | 3 |
| Payload mass range, tons | 1-5 |
| GTO injection accuracy (Ha=35,786 km, Hp=4,100 km, i=23.2 deg): | |
| - by perigee height, km | ± 40 |
| - by apogee height, km | ± 100 |
| - by inclination, deg | ± 0.1 |
| Prelaunch processing cycle, hours | 28 |
| Payload capability: Circular orbit, H=10,000 km, i=51,4 deg, tons | 4,83 |
| GSO, tons | 1.6 |
| GTO requiring 1,500 m/s to GSO, tons | 3.6 |
| Propellants | kerosene/LOX |
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