Simorgh-3 IRILV Booster Family

The Simorgh-3 displayed two stage and future three stage Simorgh-3, 4 IRILV is a continuation of the Scud-D / No-dong-A, No-dong-B and Shahab-5 / 6 / Taep’o-dong-2B / Unha-2 missile design and propulsion systems technology jointly developed by Iran and North Korea. It utilizes a new generation of liquid rocket engines developed from the No-dong-A that was subsequently flight tested under the series known as the Shahab-3A, 3B, 3C & Safir IRILV flight vehicles. Iran displayed Simorgh-3 in it's mock-up form on its “Space Technology Day” 2/3/2010. It had some obvious design errors especially in the first stage fins position (45 degrees out) as well as not giving its true height and diameters as displayed. The displayed model was not the suggested 27 meter height. The fins could very well be eliminated from the final design all together in the future because North Korea has demonstrated this viability. It's launch pad was said to be in the planning stage in early May 2010 with the suitable site identified among several available. This strongly indicated that its construction has not started in spite of some European suggestions to the contrary. It also revealed indirectly on June 8, 2010 that the Simorgh-3 IRILV Booster is expected to fly in 2012.

Suggested Simorgh-3,4 IRILV Data

Height	~24.5 to 27 Meters
Height	80.3 two stages & 88.6 feet three stages
Diameter	2.2-2.4-2.5 meters?
Diameter	7.2 – 7.8 – 8.2 feet?
Launch Mass	085 tonnes m
Launch Mass	187,425 lbs m
1 St. Launch Thrust	100 -120 - 128 tonnes f
1 St. Launch Thrust	220,500 – 264,600 - 282,240 lbs f with 4 engines
1 St. Altitude Thrust	143 tonnes f
1 St. Altitude Thrust	315,315 lbs f with four engines
2 nd. Stage Thrust	032 tonnes f vacuum.
2 nd. Stage Thrust	70,560 lbs f vacuum with two thrust chambers set on swivel gimbals mounts and one auxiliary pump engine from No-dong-B.
Control engines thrust	015 tonnes f vacuum.
Control engines thrust	33,075 lbs f
Propellants = Oxidizer	AK-27I 27% N2O4 + 73% HNO3 with Iodium inhibitor Nitrogen Tetroxide & Nitric Acid
Propellants = Fuel	TM-185 20% Gasoline, 80% Kerosene or UDMH?
Payload capacity	60 kilograms 132.3 lbs m to 500 kilometer LEO orbit or 100 kilogram satellites into 500 kilometer orbits.

This basic minimum Simorgh-3 booster represents a serious growth potential launch vehicle design concept derived from the Taep’o-dong-2B first stage and the No-dong-B derived 1.35 meter diameter Safir IRILV as its second stage. At this early stage in its development it is apparent that the displayed mock-up may not be so reliable in its design details. Only time will address this issue and show its probable resemblance to the Unha-2 booster heritage.

Speculation on Growth Potential Sigmorgh-3 Systems Design

The potential evolution of the Simorgh Family of boosters leading to possible manned spaceflight and a full range ICBM development would be consistent with previous development s in other countries.

Beyond the display of the two stage Simorgh-3 block-1, a second variant Simorgh-3/Block-II is expected to be a three stage variant based on the solid motor third stage of the Unha-2 launch vehicle.

Simorgh-4/5 IRILV {Phoenix-3}, Block-II

That could be followed by the replacement of the Simorgh-3’s second stage with a Unha-2/No-dong-B second stage 1.5 meter diameter along with the Unha-2 1.35 meter diameter third stage would constitute the Taep’o-dong-2B booster design a limited range ICBM. Below one sees the overall relationship to the Simorgh systems.

Simorgh-4 IRILV {Phoenix-3}, Block-II, Unha-2/Taep’o-dong-2 or three stage Simorgh-3?

Height	27-30-35 meters?
Height	88.6 feet -98.43 feet – 114.38feet?
Diameter	27-30-35 meters?
Diameter	7.22 – 7.8 - 8.2 feet?
Launch Mass	>85 tonnes f
Launch Mass	187,425 lbs m?
1 St. Launch Thrust	100 -120 -128 tonnes f Sea Level.
1 St. Launch Thrust	220,500 –264, 600 - 282,240 lbs f with 4 engines
1 St. Altitude thrust	143 tonnes f vacuum.
1 St. Altitude thrust	315,315 lbs f with four engines
Propellants = Oxidizer	AK-27I 27% N2O4 + 73% HNO3 with Iodium inhibitor Nitrogen Tetroxide & Nitric Acid
Propellants = Fuel	TM-185 20% Gasoline, 80% Kerosene or UDMH?
Payload Capacity	700 kilograms m
Payload Capacity	1,543.5 lbs m to 1,000 kilometer orbit (621.4 miles orbit).

Unha-2, Taep'o-dong-2B

Unha-2, Taep'o-dong-2B Final design

Simorgh-5/6 IRILV {Phoenix-3}, Block-III

After that a further design development could potentially lead to a full range ICBM and manned spaceflight system payload with a new second and third stage of constant diameter design like its first stage.

Two and Three Stage Space Boosters

Iran is moving forward with the development of not merely two stage boosters ballistic missile but is as previously predicted headed for the development of three stage boosters for space application leading the ballistic missile program developments. The three stage system is to place satellites in 1,000 kilometers orbit. Previously they orbited satellites to 250 kilometers and plan to place them in 700 kilometer orbits in 2011. It was also indicated that with in five to six years Iran would be placing telecommunications satellites into 35,000 kilometer geostationary orbit.

Simorgh-6/7 IRILV {Phoenix-3}, Block-IV

Beyond this lies the potential for a two first stage strap-on booster configuration with the constant diameter three stage core that could constitute a much larger performance triple barrel heavy booster design based on the Simorgh-5/6 concept as developed in the west under various launch vehicle programs that never made it past the concept stage. Only time will tell what form the future Iranian space program launch vehicle will evolve.

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