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| Saturn V-B |
| Fact sheet |
| Function |
Manned/unmanned LEO and Lunar launch vehicle |
| Manufacturer |
Von Braun |
| Country of origin |
United States |
| Size |
| Height |
50.00 m (164 ft) |
| Diameter |
10.06 m (33 ft) |
| Mass |
2,313,320 kg (5,099,990 lb) |
| Stages |
1.5 |
| Capacity |
| Payload to LEO |
22,600 kg (49,800 lb) |
| Launch History |
| Status |
Concept/study |
| Launch sites |
N/A |
| Total launches |
N/A |
| First Stage - S-ID Booster |
| Engines |
4 Rocketdyne F-1 |
| Thrust |
30,962.500 kN (6,960,647 lbf) |
| Burn time |
154 seconds |
| Fuel |
RP-1/LOX |
| Second Stage - S-ID Sustainer |
| Engines |
1 Rocketdyne F-1 |
| Thrust |
7,740.300 kN (1,740,089 lbf) |
| Burn time |
315 seconds |
| Fuel |
LH2/LOX |
Studied in 1968 by Marshall Space Flight Center, the Saturn V-B was considered an interesting vehicle concept because it nearly represents a single-stage to orbit booster, but is actually a stage and a half booster just like the Atlas. The booster would achieve liftoff via five regular F-1 engines; four of the five engines on the Saturn V-B would be jettisoned and could be fully recoverable, with the sustainer stage on the rocket continuing the flight into orbit. The rocket could have had a good launch capability similar to that of the Space Shuttle if it was constructed, but it never flew.
