Zenit-3SLB” launch vehicle represents Zenit rockets family using non-toxic propellants - liquid oxygen and kerosene RG-1. It was developed to launch spacecraft from Baikonur Space Center under the Land Launch Program into medium, high circular and elliptic orbits, ( including GTO and GSO) as well as to interplanetary orbits. »

ILV Zenit-3SLB

The launch vehicle was built on the basis of two-stage “Zenit-2SB” of Yuzhnoye development and DM-SL upper stage of Energia development to make “Zenit-3SLB integrated launch vehicle operated in the composition of Zenit-M space rocket complex The first launch was performed on April 28, 2009. As of July7, 2008 three launches were made.

Zenit-M rocket complex features the following advantages:

- Horizontal technology of integration and transportation allows significant simplification of technological equipment and prelaunch preparation.
- Full automatization of prelaunch processing provides minimum duration of launch preparation, the highest safety of personnel, LV independence on weather conditions and short-time refurbishment of the launch place for the next launch.
- High reliability foreseen by projecting and ensured by the proven manufacturing processes.
- Ecologically clean propellants.

Power characteristics of Zenit-3SLB at SC injections into transfer to GSO orbits

Main features of "Zenit-3SLB" ILV:

Maximum lift-off mass, t	466.2
Payload mass injected into orbits, t: GSO transfer: H=35786x230 km, i=0°	3.75
Propellant mass, t	425
Engines thrust during LV start, tf	740
Maximum acceleration during injection, g	4.0
Propellants	liquid oxygen/kerosene
Full length, m	58.65
Diameter of LV stages (1st and 2nd), m	3.9
Upper stage diameter, m	3.7
Nose fairing diameter, m	4.1
Number of stages	3
Service beginning	2008

Layout scheme

Zenit-3SLB was designed in a stacking manner with monoblock tandem scheme. The three-staged Zenit-3SLB LV contains Zenit-2SB LV and the space payload consisting of: - upper stage DM-SLB elaborated by Energia RSC; - nose fairing of 10400 mm length and 4100 mm diameter elaborated by the Lavochkin NPO; - payload.

Scheme of Zenit-3SLB space head module

Payload envelope dimension zones at the nose fairing used for Zenit-3SLB ILV

The Zenit-2SB LV is being created on the basis of Zenit-2S LV designed within the framework of the Sea Launch program and is unified with Zenit-2S. This allows Zenit-2SB LV to be used in composition of both Zenit-2SLB ILV and Zenit-3SLB ILV, as well as for Zenit-3SL ILV with minimum changes of design and configuration to be performed, if necessary, in the plant-manufacturer's conditions.