Saturn V-B

Saturn V-BFunction| Crewed/uncrewed LEO and Lunar launch vehicle

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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| 22,600 kg (49,800 lb)
Launch history
Status| Concept/study
Launch sites| Unknown
Total launches| 0
Booster stage – S-ID
Engines| 5 Rocketdyne F-1
Thrust| 30,962.50 kN (6,960,647 lbf)
Burn time| 154 s
Fuel| RP-1/LOX
First stage – S-ID Sustainer
Engines| 1 Rocketdyne F-1
Thrust| 7,740.30 kN (1,740,089 lbf)
Burn time| 315 s
Fuel| 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

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Saturn launch vehicle family

Early proposals|

* Juno V
* Saturn A-1
* A-2
* B-1

"C" series|

* Saturn C-1
* C-2
* C-3
* C-4
* C-5
* C-5N
* C-8

Saturn I series|

* Saturn I
* IB
* IB-CE
* IB-A
* IB-B
* IB-C
* IB-D
* INT-05
* INT-11
* INT-12
* INT-13
* INT-14
* INT-15
* INT-16
* INT-27
* LCB

Saturn II series|

* Saturn II
* INT-17
* INT-18
* INT-19

Saturn V series|

* Saturn V
* MLV
* V ELV
* INT-20
* INT-21
* INT-23
* INT-24
* INT-25
* Saturn-Shuttle
* Saturn V-3
* V-A
* V-B
* V-C
* V-D
* V-Centaur
* Jarvis

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