Zenit-2SLB” launch vehicle is a representative of Zenit rockets family using non-toxic propellants - liquid oxygen and kerosene RG-1. It was developed for launching spacecraft from Baikonur Space Center under the Land Launch Program into low and medium circular and elliptic orbits.

ILV Zenit-2SLB

Zenit-2SLB” LV is operated in the composition of Zenit-M space rocket complex by the International Space Services to provide launch services on a commercial basis. The first launch is scheduled on 2009.

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-2SLB at SC injections into circular orbit

Main features of "Zenith-2SLB" LV

Integrated launch vehicle	Zenit-2SLB ILV
Maximum lift-off mass, t	458.2
Payload mass injected into orbits, t: ISS: Нcirc=400 km, i=51,6°	12.03
Propellant mass, t	410
Engines thrust during LV start, tf	740
Maximum acceleration during injection, g	4.0-6.0*
Propellants	liquid oxygen/kerosene
Full length, m	57.35
Diameter of LV stages (1st and 2nd), m	3.9
Nose fairing diameter, m	3.9
Number of stages	2
Service beginning	2009
*Note: The maximum acceleration may be reduced during the injection to 4g, if necessary

The Zenit-2SLB LV 

The two-staged Zenit-2SLB LV contains Zenit-2SB LV and the space payload consisting of: - nose fairing of 13652 mm length and 3900 mm diameter developed by the Yuzhnoye SDO; - transient bay of 350 mm length and 3900 mm diameter developed by the Yuzhnoye SDO; - payload.

Scheme of Zenit-2SLB space payload

Payload envelope at the nose fairing of 3900 mm used by Zenit-2SLB ILV

The Zenit-2SB LV was built on the basis of Zenit-2S designed for Sea Launch program and unified with Zenit-2S. This allows Zenit-2SB LV to be used in Zenit-2SLB ILV and Zenit-3SLB ILV, as well as in Zenit-3SL ILV launch complexes with minimum changes of design and configuration to be performed, if necessary, at manufacturer plant.

The nose fairing of Zenit-2SB LV ( 3900 mm diameter) was developed by Yuzhnoye SDO to be fitted to Zenit LV and had been upgraded to meet the requirements for cleanliness and temperature- humidity environment of the satellite.

The transient bay of the space headmodule is a new unit designed exclusively for Zenit-2SLB LV.

Zenit-2 LV presents an optimal solution in terms of power characteristics, reliability, accuracy and cost of SC injection, which has been reached owing to utilization of developed systems and optimal planning of production process, transportation technology, prelaunch preparation and launch.