Saturn V-B

Saturn V-B
Size
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
Capacity
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 lb_f)
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 lb_f)
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.

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

This article is issued from Wikipedia. The text is licensed under Creative Commons - Attribution - Sharealike. Additional terms may apply for the media files.