Saturn IB-D

**Saturn IB-D**
Size
Function	Unmanned LEO and Lunar launch vehicle
Manufacturer	Von Braun
Country of origin	United States
Height	51.00 m (167.00 ft)
Diameter	6.61 m (21.68 ft)
Mass	1,511,980 kg (3,333,340 lb)
Stages	3
Capacity
Payload to LEO	33,000 kg (72,000 lb)
Launch history
Status	Concept/study
Launch sites	N/A
Total launches	N/A
First stage - 4x Titan UA1205
Engines	United Technologies UA1205 solid motor
Thrust	5,849.411 kN (1,315,000 lb_f)
Burn time	115 seconds
Fuel	Solid
Second stage - S-1B
Engines	8 Rocketdyne H-1
Thrust	8,241.763 kN (1,852,822 lb_f)
Burn time	155 seconds
Fuel	RP-1/LOX
Third stage - S-IVB
Engines	1 Rocketdyne J-2
Thrust	1,031.600 kN (231,913 lb_f)
Burn time	475 seconds
Fuel	LH2/LOX

Studied by Douglas Aircraft Company in 1965, this rocket consisted of a whole Saturn IB with 4 strap-on SRBs that have flown on the Titan 3E interplanetary missile carriers. All components of the vehicle have flown, but not together for this concept.

References

Lowther, Scott, Saturn: Development, Details, Derivatives and Descendants, Work in progress. Available chapters may be ordered directly from Scott Lowther at web site indicated. Accessed at: http://www.webcreations.com/ptm.

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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