Medium-lift tandem launch vehicle
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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