Safir  
Initial Operational Capability (IOC): 3 February 2009
Total Production: ?
Origin: Iran
Parent System: Safir
Initial Operational Capability (IOC): 3 February 2009
Total Production: ?
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Description: The Safir is a two-stage space launch system designed and built in Iran as part of its space program. The first launch of Safir occurred on February 3, 2009, carrying a 40 kg Omid space exploration satellite. The Omid spacecraft is expected to remain on-orbit for three months gathering data that will enable Iranian scientists to develop an operational satellite. Safir space launch systems are key for Iran to deploy a Persian Gulf surveillance capability into space to provide early warning against an attack from Israel and/or the United States of America.

Safir Specifications

Number of Stages: 2
Weight
Payload to LEO: 40 kilogram (88 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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