|
N.A.S.A. |
Saturn V | Saturn V | Saturn V | Saturn V | ||
|
Overall |
Operational | from | 18.05.1969 | 16.07.1969 | 07.12.1972 | 14.05.1973 |
| to | ||||||
| Orbital flights | Apollo 10 | Apollo 11 | Apollo 17 | Skylab | ||
| Payload weight | t | 42.863 | 43.869 | 46.780 | 102.87 | |
| Gross liftoff weight | t | 2945.19 | 2,928.53 | 2,962.38 | 2,857.15 | |
| Gross propellant weight | t | 2,709.88 | 2,715.85 | 2,747.72 | 2,588.85 | |
| Total length | m | 110.71 | 110.71 | 110.71 | 101.64 | |
| Max. diameter (span) | m | 18.00 | 18.00 | 18.00 | 18.00 | |
| Total liftoff thrust (s.l.) | kN | 34,478 | 34,478 | 34,478 | 34,478 | |
| Total impulse (vac) | MN*s | 8,733.8 | 8,748.8 | 8,853.2 | 8,277.6 | |
|
Fairing |
Total length | m | 24.94 | 24.94 | 24.94 | 34.73 |
| Diameter | m | 6.62 | 6.62 | 6.62 | 6.62 | |
| Total weight (Adapter+LES) | t | 5.890 | 5.890 | 5.860 | - | |
| SM |
Name |
Service Modul | Service Modul | Service Modul | ||
| Length | m | 4.48 (7.49 | 4.48 (7.49) | 4.48 (7.49) | ||
| Diameter | m | 3.91 | 3.91 | 3.91 | ||
| Liftoff weight | t | 23.270 | 23.571 | 24.514 | ||
| Propellant weight | t | 17.170 | 17.570 | 18.505 | ||
| Engines | AJ-10-137 | AJ-10-137 | AJ-10-137 | |||
| Propellant | Aerozin50/N2O4 | Aerozin50/N2O4 | Aerozin50/N2O4 | |||
| Total thrust (vac) | kN | 97.86 | 97.86 | 97.86 | ||
| Specific impulse (vac) | N*s/kg | 2956 | 2956 | 2956 | ||
| Burn time | s | 520 | 531 | 559 | ||
| Total impulse (vac) | MN*s | 50.8 | 52.0 | 54.7 | ||
| Stage 3 |
Name |
S-4B | S-4B | S-4B | Skylab | |
| Length | m | 18.86 | 18.86 | 18.86 | ||
| Diameter | m | 6.62 | 6.62 | 6.62 | ||
| Liftoff weight | t | 116.76 | 120.12 | 123.20 | ||
| Propellant weight | t | 103.53 | 106.83 | 108.11 | ||
| Engines | Rock. J-2 | Rock. J-2 | Rock. J-2 | |||
| Propellant | LH2/LOX | LH2/LOX | LH2/LOX | |||
| Total thrust (vac) | kN | 876 | 876 | 876 | ||
| Specific impulse (vac) | N*s/kg | 4173 | 4173 | 4173 | ||
| Burn time | s | 493 | 509 | 515 | ||
| Total impulse (vac) | MN*s | 432.0 | 445.8 | 451.1 | ||
| Stage 2 |
Name |
S-2 | S-2 | S-2 | S-2 | |
| Length | m | 24.84 | 24.84 | 24.84 | 24.84 | |
| Diameter | m | 10.06 | 10.06 | 10.06 | 10.06 | |
| Liftoff weight | t | 480.43 | 478.63 | 486.28 | 510.76 | |
| Propellant weight | t | 444.18 | 444.18 | 451.83 | 474.51 | |
| Engines | 5 | Rock. J-2 | Rock. J-2 | Rock. J-2 | Rock. J-2 | |
| Propellant | LH2/LOX | LH2/LOX | LH2/LOX | LH2/LOX | ||
| Total thrust (vac) | kN | 5,160 (3,505) | 5,160 (3,505) | 5,160 (3,505) | 5,160 (3,505) | |
| Specific impulse (vac) | N*s/kg | 4161 (4173) | 4161 (4173) | 4161 (4173) | 4161 (4173) | |
| Burn time | s | 297+91 | 297+91 | 297+100 | 297+127 | |
| Total impulse (vac) | MN*s | 1,849.3 | 1,849.3 | 1,881.2 | 1,975.9 | |
|
Stage 1 |
Name | S-1C | S-1C | S-1C | S-1C | |
| Length | m | 42.07 | 42.07 | 42.07 | 42.07 | |
| Diameter | m | 10.06 | 10.06 | 10.06 | 10.06 | |
| Liftoff weight | t | 2,275.98 | 2,278.25 | 2,300.27 | 2,245.32 | |
| Propellant weight | t | 2,145.00 | 2,147.27 | 2,169.29 | 2,114.34 | |
| Engines | 5 | Rock. F-1 | Rock. F-1 | Rock. F-1 | Rock. F-1 | |
| Propellant | Kerosene/LOX | Kerosene/LOX | Kerosene/LOX | Kerosene/LOX | ||
| Total thrust (s.l.) | kN | 34,478 (27,582) | 34,478 (27,582) | 34,478 (27,582) | 34,478 (27,582) | |
| Specific impulse (s.l.) | N*s/kg | 2550 | 2550 | 2550 | 2550 | |
| Burn time | s | 140+21 | 142+21 | 142+23 | 142+18 | |
| Total impulse (vac) | MN*s | 6,401.7 | 6,401.7 | 6,466.2 | 6,301.7 | |