Saturn V-B

From Wikipedia, the free encyclopedia
Jump to: navigation, search
Saturn V-B
Function Manned/unmanned LEO and Lunar launch vehicle
Manufacturer Von Braun
Country of origin United States
Height 50.00 m (164 ft)
Diameter 10.06 m (33 ft)
Mass 2,313,320 kg (5,099,990 lb)
Stages 1.5
Payload to LEO 22,600 kg (49,800 lb)
Launch history
Status Concept/study
Launch sites N/A
Total launches N/A
First stage - S-ID Booster
Engines 5 Rocketdyne F-1
Thrust 30,62.500 kN (6,960,647 lbf)
Burn time 154 seconds
Fuel RP-1/LOX
Second stage - S-ID Sustainer
Engines 1 Rocketdyne F-1
Thrust 7,740.300 kN (1,740,089 lbf)
Burn time 315 seconds
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.