Saturn IB-D

Saturn IB-D

Function	Unmanned LEO and Lunar launch vehicle
Manufacturer	Von Braun
Country of origin	United States
Size
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 lbf)
Burn time	115 seconds
Propellant	Solid
Second stage S-1B
Engines	8 Rocketdyne H-1
Thrust	8,241.763 kN (1,852,822 lbf)
Burn time	155 seconds
Propellant	RP-1/LOX
Third stage - S-IVB
Engines	1 Rocketdyne J-2
Thrust	1,031.600 kN (231,913 lbf)
Burn time	475 seconds
Propellant	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: https://web.archive.org/web/20070521083808/http://www.webcreations.com/ptm.