|
N.A.S.A. |
Saturn IB | Saturn IB | Saturn IB | Saturn IB | ||
|
Overall |
Operational | from | 22.01.1968 | 11.10.1968 | 14.09.1973 | 15.07.1975 |
| to | 16.11.1974 | |||||
| Orbital flights | Apollo 5 | Apollo 7 | Skylab (3) | ASTP | ||
| Payload weight | t | 14.15 (LM) | 4.990 (CM) | 5.048 (CM) | 5.830 | |
| Gross liftoff weight | t | 566.89 | 589.74 | 592.9 | 596.41 | |
| Gross propellant weight | t | 499.76 | 521.79 | 525.8 | 526.66 | |
| Total length | m | 56.16 | 68.09 | 68.09 | 68.09 | |
| Max. diameter (span) | m | 12.41 | 12.41 | 12.41 | 12.41 | |
| Total liftoff thrust (s.l.) | kN | 7,117 | 7,117 | 7,117 | 7,117 | |
| Total impulse (vac) | MN*s | 1,423.8 | 1,636.0 | 1,649.7 | 1,652.4 | |
|
Fairing |
Total length (with LES) | m | 13.01 | 11.93 | 11.93 | 11.93 |
| Diameter | m | 6.52 | 6.52-3.91 | 6.52-3.91 | 6.52-3.91 | |
| Total weight (Adapter + LES) | t | 1.85 | 5.860 | 5.860 | 6.073 | |
| SM |
Name |
Service Modul | Service Modul | Service Modul | ||
| Length | m | 4.48 | 4.48 | 4.48 | ||
| Diameter | m | 3.91 | 3.91 | 3.91 | ||
| Liftoff weight | t | 11.425 | 6.062 | 6.698 | ||
| Propellant weight | t | 5.462 | 0.993 | 1.890 | ||
| Engines | Aerojet | Aerojet | Aerojet | |||
| 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 | 165 | 30 | 57 | ||
| Total impulse (vac) | MN*s | 16.1 | 2.9 | 5.6 | ||
| Stage 2 |
Name |
S-4B | S-4B | S-4B | S-4B | |
| Length (+adapter) | m | 13.01 | 21.54 | 21.54 | 21.54 | |
| Diameter | m | 6.52 | 6.52 | 6.52 | 6.52 | |
| Liftoff weight | t | 116.21 | 117.11 | 119.61 | 119.61 | |
| Propellant weight | t | 103.43 | 104.32 | 106.83 | 106.83 | |
| Engines | 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 | 1,001 (823) | 1,001 (823) | 1,001 (823) | 1,001 (823) | |
| Specific impulse (vac) | N*s/kg | 4168 (4217) | 4168 (4217) | 4168 (4217) | 4168 (4217) | |
| Burn time | s | 297+165 | 297+170 | 297+183 | 297+183 | |
| Total impulse (vac) | MN*s | 324.7 | 436.4 | 447.3 | 447.3 | |
|
Stage 1 |
Name | S-1B | S-1B | S-1B | S-1B | |
| Length (+adapter) | m | 30.14 | 30.14 | 30.14 | 30.14 | |
| Diameter | m | 6.62 | 6.62 | 6.62 | 6.62 | |
| Liftoff weight | t | 434.68 | 450.35 | 456.32 | 456.32 | |
| Propellant weight | t | 396.33 | 412.00 | 417.97 | 417.97 | |
| Engines | 8 | Rock. H-1 | Rock. H-1 | Rock. H-1 | Rock. H-1 | |
| Propellant | Kerosene/LOX | Kerosene/LOX | Kerosene/LOX | Kerosene/LOX | ||
| Total thrust (s.l.) | kN | 7,117 (3,558) | 7,117 (3,558) | 7,117 (3,558) | 7,117 (3,558) | |
| Specific impulse (s.l.) | N*s/kg | 2574 | 2574 | 2574 | 2574 | |
| Burn time | s | 135+7 | 141+7 | 141+10 | 141+10 | |
| Total impulse (vac) | MN*s | 1,099.1 | 1,147.9 | 1,199.5 | 1,199.5 | |