Shahab 3 Credit - © Mark Wade

It had originally been claimed by Ali Shamkharni, the Iranian Minister of Defence, that the Iranian Shahab-4 missile would be used as a satellite launcher. The Shahab-4 was abandoned, but reports came in late 2003 that a stretched and improved version of the Shahab-3 would be the basis for an Iranian indigenous satellite launcher. First attempt was planned for 2005.

In November 2004 US intelligence sources stated that the version of the missile used in 2004 tests had been stretched 15% and equipped with a larger payload fairing, indicating possible preparations for the long-announced Iranian indigenous satellite launch. A stretched Shahab-3 with improved performance, topped with two upper stages, would be equivalent to the French Diamant launcher of the 1960's. It would certainly be capable of orbiting the 60 kg Mesbah satellite mentioned in the press, and possibly the 170 kg mentioned for the follow-on satellite.

Photographs had circulated since 1998 of a Shahab-3 outfitted as the 'Iris' satellite launcher, complete with an improbably large payload fairing. This is unlikely unless the Iranians planned a leap to Lox/LH2 upper stage engine technology for the upper stage. This may not have been as improbably as it may sound. The Chinese achieved a similar feat with their CZ-3 upper stage in 1984, becoming the third nation to fly this technology.

The following are two possible reconstructions:

Storable liquid propellant first and second stages, solid propellant kick stage.

Stage Gross Mass Empty Mass Isp Delta-V
              kg         kg vac     m/s
    1     15,000      1,350 250   3,770 
    2      2,000        200 255   3,528 
    3        300         50 200   2,102 
Payload       80                  9,400 

Storable liquid propellant first stage, Lox/LH2 upper stage.

Stage Gross Mass Empty Mass Isp Delta-V
              kg         kg vac     m/s
    1     15,000      1,350 250   3,760 
    2      2,000        200 425   5,774 
Payload      400                  9,534 

LEO Payload: 60 kg (132 lb). to: 900 km Orbit. at: 107.00 degrees. Liftoff Thrust: 255.000 kN (57,326 lbf). Total Mass: 18,000 kg (39,000 lb). Core Diameter: 1.20 m (3.90 ft). Total Length: 19.00 m (62.00 ft). Boost Propulsion: Storable liquid rocket. Guidance: Inertial.

• Federation of American Scientists Web Site, . Accessed at: http://www.fas.org/.

• Bermudez, Joseph S, Jr, A History of Ballistic Missile Development in the DPRK, Center for Nonproliferation Studies, CNS Occ. Papers #2, 2000.. Accessed at: http://cns.miis.edu/pubs/opapers/op2/index.htm.

• Wire service and TV news reports..