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Launch vehicle ZENIT-3SL

The launch vehicle (LV) is designed for injection of average mass payloads to medium and high circular and elliptic near Earth orbits, including GTO and GEO, as well as flyaway trajectories (orbit inclination of ±180 deg). The LV is launched out of floating platform in aquatic area of the Pacifi c Ocean.

The three-stage vehicle is based on the two-stage launch vehicle “Zenit-2” (designed by “Yuzhnoye” SDO), upper stage DM (designed by “Energia” RSC), and payload unit (designed by “Boeing”).

Specifications

Maximum launching mass, t

473

Mass of payload injected to regular geo-transition orbit

(200 km.35 786 km, inclination = 0 deg), t

 

6,1

Engines thrust at launch, tf

740

Maximum acceleration during injection, units

4

Accuracy of payload injection to regular geo-transition orbit:

 

perigee altitude, km

±10

apogee altitude, km

±80

inclination, deg

±0,25

Full length, m

59,6

Stage case diameter, m

3,9

Upper stage diameter, m

3,7

Payload fairing diameter, m

4,15