| Islamic Republic Iran |
Simorgh (Unha-1) |
Simorgh |
Simorgh+ |
|||||
|
Overall Vehicle |
Operational | from | 19.04.2016 | 27.07.2017 | ||||
|
|
to | 30.12.2021 | ||||||
| Orbital flights | 1 | 4 | ||||||
| Payload weight | t | LEO | - | LEO | - | LEO | ~0.100 | |
| Gross liftoff weight | t | ~84.80 | ~84.80 | ~85.80 | ||||
| Gross propellant weight | t | 70.51 | 70.51 | 71.74 | ||||
| Total length | m | 25.974 | 25.974 | ~26.50 | ||||
| Max. diameter (span) | m | |||||||
| Total liftoff thrust (s.l.) | kN | 1,271.0 | 1,271.0 | 1,332.7 | ||||
| Total impulse (vac) | MN*s | 188.4 | 196.0 | 198.2 | ||||
|
Fairing |
Total length | m | ~3.20 | ~3.20 | ~3.20 | |||
| Diameter | m | 1.50 | 1.50 | 1.50 | ||||
| Total weight | t | ~0.12 | ~0.12 | ~0.12 | ||||
| Stage 3 | Name | Saman-1 | ||||||
| Length | m |
Without third stage no Orbit |
Without third stage no Orbit |
~1.25 | ||||
| Diameter | m | ~0.60 | ||||||
| Liftoff weight | t | ~0.315 | ||||||
| Propellant weight | t | 0.185 | ||||||
| Engines | ||||||||
| Propellant | solid | |||||||
| Total thrust (vac) | kN | 13.0 (av.) | ||||||
| Specific impulse (vac) | N*s/kg | 2810 | ||||||
| Burn time | s | 40 | ||||||
| Total impulse (vac) | MN*s | 0.52 | ||||||
| Stage 2 |
Name |
|||||||
| Length (+adapter) | m | ~5.00 | ~5.00 | ~5.50 | ||||
| Diameter | m | 1.50 | 1.50 | 1.50 | ||||
| Liftoff weight | t | ~ 8.96 | ~ 8.96 | ~9.60 | ||||
| Propellant weight | t | ~7.47 | ~7.47 | ~8.00 | ||||
| Engines | 2 LRE-4 (4) | 2 LRE-4+ (4) | 2 LRE-4++ (4) | |||||
| Propellant | UDMH / AK-27 | UDMH / N2O4 | UDMH / N2O4 + | |||||
| Total thrust (vac) | kN | 68.2 | 70.8 | ~71.6 | ||||
| Specific impulse (vac) | N*s/kg | ~2736 | ~2844 | ~2864 | ||||
| Burn time | s | 300 | 300 | 320 | ||||
| Total impulse (vac) | MN*s | 20.4 | 21.2 | 22.9 | ||||
|
Stage 1 |
Name | |||||||
| Length (+ adapter) | m | 17.816 | 17.816 | 17.816 | ||||
| Diameter | m | 2.40 | 2.40 | 2.40 | ||||
| Liftoff weight | t | ~75.65 | ~75.65 | ~75.65 | ||||
| Propellant weight | t | ~63.04 | ~63.04 | ~63.04 | ||||
| Engines | Nodong (4) | Nodong+ (4) | Nodong+ (4) | |||||
| Propellant | UDMH /AK-27 | UDMH /N2O4 | UDMH /N2O4 | |||||
| Total thrust (s.l.) | kN | 1,137.6 (+133.4) | 1,192.8 (+139.9) | 1,192.8 (+139.9) | ||||
| Specific impulse (s.l.) | N*s/kg | ~2422 | ~2540 | ~2540 | ||||
| Burn time | s | 120 | 120 | 120 | ||||
| Total impulse (vac) | MN*s | 168.0 | 174.8 | 174.8 | ||||