Shahab 3 Credit - © Mark Wade

Orbital launch vehicle. Family:

Iranian derivative of North Korean No Dong 1 intermediate range ballistic missile, evolved incrementally with Russian assistance into a longer-range missile and the first stage of an orbital launch vehicle.

On 7 July 2003 Iranian state radio reported that the final trials test had been conducted a few weeks earlier and the missile had been accepted by the military. It was also reported that the larger Shahab 4 missile had been cancelled, since the Shahab 3 had been provided with a greater payload in its place. Western sources indicated Russian technology was used in the improvement of the Shahab 3.

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.

Manufacturer: Korea North. Launches: 11. Failures: 2. Success Rate: 81.82%. First Launch Date: 1998-07-22. Last Launch Date: 2008-02-04. Launch data is: continuing. Version:

Shahab 3. Intermediate range ballistic missile. Status: Active.

Initial version of the missile that began flight tests in 1998.

Launches: 10. Failures: 2. First Launch Date: 1998-07-22. Last Launch Date: 2006-12-01. Apogee: 150 km (90 mi). Liftoff Thrust: 255.000 kN (57,326 lbf). Total Mass: 14,500 kg (31,900 lb). Core Diameter: 1.19 m (3.90 ft). Total Length: 14.82 m (48.61 ft). Standard warhead mass: 700 kg (1,540 lb). Maximum range: 1,200 km (700 mi). Boost Propulsion: Storable liquid rocket. Guidance: Inertial.

• Stage1: 1 x Shahab 3. Gross Mass: 15,100 kg (33,200 lb). Empty Mass: 2,000 kg (4,400 lb). Motor: 1 x Nodong. Thrust (vac): 255.000 kN (57,326 lbf). Burn time: 110 sec. Length: 16.00 m (52.00 ft). Diameter: 1.30 m (4.20 ft). Propellants: Nitric acid/UDMH.

Total Mass: 26,900 kg (59,300 lb). Core Diameter: 1.65 m (5.40 ft). Total Length: 22.81 m (74.82 ft). Standard warhead mass: 1,400 kg (3,000 lb). Maximum range: 2,000 km (1,200 mi). Boost Propulsion: Storable liquid rocket. Guidance: Inertial. Version:

Shahab SLV. Status: In development. Other Designations: Shahab 6.

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 

1997 February - Russo-Iranian technical assistance in rocketry Israel provided US intelligence agencies with a copy of a $7 million contract between NPO Trud and Iran for equipment related to the R-12 IRBM. Other Russian contributions included wind tunnel, software, and mathematical modelling services from TsAGI, Polyus for laser gyro systems, and development of a solid-fuel capability.

1998 July 22 - Sriharikota -. FAILURE: Failure. Test mission Agency: Iran. Apogee: 0 km ( mi).

1998 August - Iranian satellite launcher mockup exhibited Iranian television showed what appeared to be a mock-up of a clam-shell nosecone with a small satellite inside and a model of a space launch vehicle with a bulbous payload section, apparently based upon the Shahab 3 joint North Korean/Iranian IRBM.

2000 July 15 - Sriharikota -. Test mission Agency: Iran. Apogee: 150 km (90 mi).

2000 September 21 - Sriharikota -. Shahab 3 Shahab-3D FAILURE: Failure. Test mission Agency: Iran. Apogee: 150 km (90 mi).

2002 May 5 - Sriharikota -. Test mission Agency: Iran. Apogee: 150 km (90 mi).

2003 June 1 - Emamshahr -. Shahab 3 Test Launch 6 Agency: Revolutionary Guard Air Force. Missile built by Shahid Hemmat IG

2004 August 11 - Sriharikota -. Agency: Iran. Apogee: 150 km (90 mi). Missile demonstration flight. Stretched Shahab-3 launched into Dasht-E-Kavir desert.

2004 October 20 - Sriharikota -. Agency: Iran. Apogee: 150 km (90 mi). Missile demonstration flight. Stretched Shahab-3 launched into Dasht-E-Kavir desert.

2006 May 22 - Sriharikota -. Shahab 3D test Agency: Iran. Apogee: 150 km (90 mi).

2006 November 2 - Sriharikota -. Iranian multiple missile firings Agency: Iran. Apogee: 150 km (90 mi). The Iranians fired at least one Shahab-3 and "dozens of" Shahab-2, Zolfaghar-73, Scud B, Fath-110 and Zelzal missiles in a mass firing demonstration to kick off their Great Prophet 2 military exercise. It marked the first firing of the Shahab 3 by troops on exercise as opposed to a test flight. The Shahab 2 was reported to have demonstrated a 1,400-bomblet cluster bomb warhead.

2006 December 1 - Sriharikota -. Shahab 3 Sounding rocket Agency: Iran. Apogee: 150 km (90 mi).

2008 February 4 - Iran tests satellite launcher. Iran's president tours new space launch facilities and a rocket is launched, said by some to be a test version of the Shahab satellite vehicle without operative upper stages.