Medium-lift tandem launch vehicle

Description
Features
Graphs

The Zenit-3SLBF Integrated Launch Vehicle is designed to deliver medium-weight spacecraft into mean and high circular and elliptical near-earth orbits, including geosynchronous transfer and geostationary orbits, as well as escape trajectories.  

The Zenit-3SLBF Integrated Launch Vehicle is included into the Zenit rocket family operating on non-toxic propellant components (liquid oxygen and kerosene RG-1). It is developed within the framework of the Land Launch program for spacecraft launches from the Baikonur Cosmodrome (Kazakhstan). The System is capable to provide up to 12 launches per year (including up to 7 launches with the upper stage). 

The Zenit-3SLBF Integrated Launch Vehicle is developed on the basis of the Zenit-2SLB Integrated Launch Vehicle (developed by Yuzhnoye SDO), Fregat-SB Upper Stage and fairing (developed by NPO Lavochin). The first launch took place on January 20, 2011. Total 4 missions were fired, all a success.

Basic Specifications

Number of stages

3

Dimensions, mm 

Length 

Stage diameter

Fairing diameter

 

55 250

3 900

4 100

Launch mass, tons

462

Propellants

Oxidizer

Fuel

 

Liquid oxygen

Kerosene

Thrust, ton-force

Stage 1

Stage 2

Stage 3

 

806,4

101,1

2,0

Maximum payload capability, tons

Circular orbit: (Нc= 1000 km)

Geostationary transfer orbit: (H=35786?4100 km, i=23.2°)

 

5,5

4,0

Injection accuracy

Circular orbit (Нc= 10000 km)

Altitude, km

Inclination, deg

Geostationary transfer orbit (H=4000 km)

Apogee height, km

Perigee height, km

Inclination, deg

 

 

±25

±0,06

 

±40

 

±100

±0,1

Maximum g-load

4,0

Payload fairing cleanliness class (FED STD 209E)

100 000

 

Zenit-3SLBF Payload Capability into Circular Orbit (launch from Baikonur)

Zenit-3SLBF Payload Capability into GTO (launch from Baikonur)

Payload Accommodation Area with 10.4-m High Payload Fairing

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