Saturn V-B

Saturn V-B

Function	Crewed/uncrewed LEO and Lunar launch vehicle
Country of origin	United States
Size
Height	50 m (164 ft)
Diameter	10 m (33 ft)
Mass	2,313,320 kg (5,099,990 lb)
Stages	1.5
Capacity
Payload to LEO
Mass	22,600 kg (49,800 lb)
Launch history
Status	Concept/study
Launch sites	Unknown
Total launches	0
Booster stage – S-ID
Powered by	5 Rocketdyne F-1
Maximum thrust	30,962.50 kN (6,960,647 lbf)
Burn time	154 s
Propellant	RP-1/LOX
First stage – S-ID Sustainer
Powered by	1 Rocketdyne F-1
Maximum thrust	7,740.30 kN (1,740,089 lbf)
Burn time	315 s
Propellant	RP-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

• Saturn-Shuttle

Further reading

• Saturn V-B refers to Boeing study