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Saturn V-B

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This is an old revision of this page, as edited by Rod57 (talk | contribs) at 14:36, 9 August 2019 (== Further reading == * [http://www.astronautix.com/s/saturnv-b.html ] refers to Boeing study). The present address (URL) is a permanent link to this revision, which may differ significantly from the current revision.

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)
Stages2
Capacity
Payload to LEO
Mass22,600 kg (49,800 lb)
Launch history
StatusConcept/study
Launch sitesUnknown
Total launches0
First stage – S-ID Booster
Powered by5 Rocketdyne F-1
Maximum thrust30,962.50 kN (6,960,647 lbf)
Burn time154 s
PropellantRP-1/LOX
Second stage – S-ID Sustainer
Powered by1 Rocketdyne F-1
Maximum 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