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Initial Operational Capability (IOC): 1999
Total Production: ?
Origin: Russia, Ukraine and United States of America
Corporations: Boeing, NPO Energomash and Yuzhnoye
Parent System: Zenit
Initial Operational Capability (IOC): 1985
Total Production: ?
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Description: The Zenit is a two-stage liquid fueled rocket introduced in 1985 and capable of carrying a 30,000 lb (13,600 kg) payload to a Low Earth Orbit (LEO). The Zenit-3SL is a three-stage version of Zenit launch vehicle consisting of a liquid oxygen/kerosene fueled Zenit-2S launch vehicle (RD-171, RD-120 and RD-8 engines), Block DM-SL upper stage (11D58M), and payload unit containing spacecraft. Design Bureau Yuzhnoye, Production Association Yuzhmashzavod, Boeing and RSC Enegia. The Zenit-3SL launch vehicle is available for commercial customers through the Sea Launch platform to be launched from the equator saving propellant to put the payload into orbit. It is capable of carrying a 13,200 lb (6,000 kg) payload into a Geosynchronous Transfer Orbit (GTO).

Zenit-3SL Specifications

Crew: 0
Height: 60 meter (2,348 inch)
Rocket Diameter: 4.27 meter
Max Lift-off Weight: 471 ton (1,038,360 pound)
Payload to GTO: 6,000 kilogram (13,228 pound)
Payload to LEO: 13,600 kilogram (29,982 pound)
CEP: Circular Error Probable
Meters (m)   Kilometers (km)   Nautic Miles (nm)   Inch (in)   Yard (yd)   Foot (ft)   Millimeter (mm)
Pound (lb)   Kilogram (kg)   kN (KiloNewton)   Ton (t)
Meters per Second (mps)   Kilometers per Hour (kph)   Knot (kt)   Miles per Hour (mph)
Liter (l)   Galon (gl)
Year (yr)   Minutes (min)   Second (sec)
Shaft-Horse-Power (shp)

Operators & Related Equipment


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Propulsion Systems
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