Simorgh
Stage · Iran
Original archive entry. The text, images and links below are kept as they were written.
Iran's second orbital launch vehicle, 2.5 m first stage diameter. Payload capability 350 kg to low earth orbit.
Despite sharing a common diameter, Simorgh's first stage was significantly different to that of the North Korean Unha-2/3. The first stage was about 1.5 m longer and the tank volume ratio O/F was about 1.4 (Unha-2/3 was 1.6). Primary propulsion was a cluster of four Nodong engines, arranged like the unrealized Unha-1. First stage steering was by four vernier motors, each with their own turbopump, again different from those on the Unha-2/3. The second stage was a longer, larger diameter version of the Safir-1 upper stage, using four four engines of the LRE-4 (4D10V) fed by two turbopumps. A third stage was needed to kick the payload to orbital velocity, perhaps using the Saman-1 solid rocket motor.
More at: Simorgh.
Related
- Family
- orbital launch vehicle
- Country
- Iran
- Launch Sites
- Semnan
- Bibliography
- 13407
Chronology
2 events
2017 July 27
09:29 GMT - . Launch Site: Semnan. Launch Complex: Semnan LC31. LV Family: Unha. Launch Vehicle: Simorgh.- Simorgh Test payload - . Payload: -. Nation: Iran. COSPAR: 2017-F04. See Toloo ?. Orbital launch attempt. Impacted Dasht-e-Lut?..
2019 January 15
00:29 GMT - . Launch Site: Semnan. Launch Complex: Semnan SC. LV Family: Unha. Launch Vehicle: Simorgh.- Payam - .
Nation: Iran.
Type: Comms/Imag F. COSPAR: 2019-F01A.
See Payam-e Amirkabir (AUTSAT 1, Amir-Kabir 1). The third stage failed to operate correctly and the 100-kg-class satellite payload, "Payam", failed to reach orbit. Planned orbit was 500 x 500 km x 55 deg. If the third stage did not fire at all, the payload probably fell in the Indian Ocean, possibly about 1000 km west of the Cocos Islands.