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.[1]: 1102 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.

## Contents

* 1 Concept
* 2 See also
* 3 References
* 4 Further reading

## Concept

With use of the Saturn V vehicle during Apollo, NASA began considering plans for a hypothesized evolutionary Saturn V family concept that spans the earth orbital payload spectrum from 50,000 to over 500,000 lbs. The "B" derivative of the Saturn V was a stage and one- half version of the then current S-IC stage and would become the first stage in an effective and economical assembly of upper stages of the evolutionary Saturn family.

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.[1] The vehicle would be capable of a LEO payload of 50,000 lb with a standard S-IC stage length of 138 f. Increases in the length of the stage could significantly increase this capability.[1]: 1103

## See also

* Saturn-Shuttle

## References

1. ↑ 1.0 1.1 1.2 Scott and, Ronald D.; Corcoran, William L. (1968). "Saturn V Derivatives". SAE Transactions (SAE International) 77: 1099–1112. https://www.jstor.org/stable/44565202. Retrieved January 7, 2023.

## Further reading

* Saturn V-B refers to Boeing study

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* t
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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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