| NPO Yuzhnoye (Ukraine), I.C. Land Launch |
Zenit 2 |
Zenit 2M |
Zenit 3SLB | Zenit 3F (G) | ||||||
|
Overall Vehicle |
Operational | from | 13.04.1985 | 22.05.1990 | 28.04.2008 | 20.01.2011 | ||||
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to | 23.11.1988 | 29.06.2007 | 31.08.2013 | 26.12.2017 | |||||
| Orbital flights | 13 | 24 | 6 | 5 | ||||||
| Max. payload weight | t | LEO | 13.50 | LEO | 13.74 | GTO | 3.80 | GEO | 1.80 | |
| Gross liftoff weight | t | 454.10 | 454.35 | 469.15 | 455.60 | |||||
| Gross propellant weight | t | 401.81 | 401.81 | 423.85 | 414.02 | |||||
| Total length | m | 57.00 | 57.00 | 59.46 | 54.35 | |||||
| Max. diameter (span) | m | 3.90 | 3.90 | 4.10 | 3.90 | |||||
| Total liftoff thrust (s.l.) | kN | 7,257 | 7,257 | 7,257 | 7,257 | |||||
| Total impulse (vac) | MN*s | 1,338.2 | 1,338.2 | 1,414.0 | 1,378.3 | |||||
|
Fairing |
Total length | m | 11.15/13.65 | 11.15/13.65 | 10.40 | 10.70 | ||||
| Diameter | m | 3.90 | 3.90 | 4.10 | 4.10 | |||||
| Total weight | t | 2.10/2.30 | 2.10/2.30 | 1.80 | 1.85 | |||||
| Stage 3 | Name | Block DM-SLB | Fregat-SB | |||||||
| Length | m | 5.71 | ||||||||
| Diameter | m | 3.70 | ||||||||
| Liftoff weight (+adapters) | t | 18.35 | 12.00 | |||||||
| Propellant weight | t | 14.57 | 10.00 | |||||||
| Engines | RD-58Z | S5.92 l.n. | ||||||||
| Propellant | Kerosene/LOX | UDMH/N2O4 | ||||||||
| Total thrust (vac) | kN | 79.46 | 20.01 | |||||||
| Specific impulse (vac) | N*s/kg | 3492 | 3268 | |||||||
| Burn time | s | 640 | 1,635 | |||||||
| Total impulse (vac) | MN*s | 50.9 | 32.7 | |||||||
| Stage 2 | Name | |||||||||
| Length | m | 10.41 | 10.41 | 10.41 | 10.71 | |||||
| Diameter | m | 3.90 | 3.90 | 3.90 | 3.90 | |||||
| Liftoff weight | t | 89.40 | 89.40 | 90.85 | 90.10 | |||||
| Propellant weight | t | 80.90 | 80.90 | 82.49 | 81.74 | |||||
| Engines | RD-120 | RD-120 | RD-120 forced | RD-120 forced | ||||||
| Propellant | Kerosene/LOX | Kerosene/LOX | Kerosene/LOX | Kerosene/LOX | ||||||
| Total thrust (vac) | kN | 833.6 (+78.5) | 833.6 (+78.5) | 912.0 (+78.5) | 912.0 (+78.5) | |||||
| Specific impulse (vac) | N*s/kg | 3432 | 3432 | 3432 | 3432 | |||||
| Burn time | s | 297 (375) | 297 (375) | 277 (375) | 274 (375) | |||||
| Total impulse (vac) | MN*s | 277.0 | 277.1 | 282.5 | 279.9 | |||||
| Stage 1 |
Name |
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| Length | m | 32.94 | 32.94 | 32.94 | 32.94 | |||||
| Diameter | m | 3.90 | 3.90 | 3.90 | 3.90 | |||||
| Liftoff weight | t | 348.90 | 348.90 | 354.35 | 349.85 | |||||
| Propellant weight | t | 320.91 | 320.91 | 326.79 | 322.28 | |||||
| Engines (Chambers) | RD-171 (4) | RD-171M (4) | RD-171M (4) | RD-171M (4) | ||||||
| Propellant | Kerosene/LOX |
Kerosene/LOX |
Kerosene/LOX |
Kerosene/LOX |
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| Total thrust (s.l.) | kN | 7,256.9 | 7,256.9 | 7,256.9 | 7,256.9 | |||||
| Specific impulse (s.l.) | N*s/kg | 3033 | 3033 | 3033 | 3033 | |||||
| Burn time | s | 134.1 | 134.1 | 136.6 | 134.7 | |||||
| Total impulse (vac) | MN*s | 1,061.2 | 1,061.2 | 1,080.6 | 1,065.7 | |||||
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Note: RD-171 is throttled to 50% thrust after 114 sec |
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