Saturn V-B

Summary

Saturn V-B
FunctionCrewed/uncrewed LEO and Lunar launch vehicle
Country of originUnited States
Size
Height50 m (164 ft)
Diameter10 m (33 ft)
Mass2,313,320 kg (5,099,990 lb)
Stages1.5
Capacity
Payload to LEO
Mass22,600 kg (49,800 lb)
Launch history
StatusConcept/study
Launch sitesUnknown
Total launches0
Booster stage – S-ID
Engines5 Rocketdyne F-1
Thrust30,962.50 kN (6,960,647 lbf)
Burn time154 s
PropellantRP-1/LOX
First stage – S-ID Sustainer
Engines1 Rocketdyne F-1
Thrust7,740.30 kN (1,740,089 lbf)
Burn time315 s
PropellantRP-1/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.

See also

Further reading

  • Saturn V-B refers to Boeing study