Engineering:Saturn IB-D

Saturn IB-D

Function	Uncrewed LEO and Lunar launch vehicle
Manufacturer	Von Braun
Country of origin	United States
Size
Height	51.00 m (167.32 ft)
Diameter	6.61 m (21.7 ft)
Mass	1,511,980 kg (3,333,350 lb)
Stages	2
Capacity
Payload to LEO	33,000 kg (73,000 lb)
Launch history
Status	Concept/study
Launch sites	N/A
Total launches	N/A
Boosters – Titan UA1205
No. boosters	4
Motor	1 United Technologies UA1205
Thrust	5,849.411 kN (1,315,000 lbf)
Specific impulse	263 s (2.58 km/s)
Burn time	115 seconds
Fuel	PBAN
First stage – S-1B
Engines	8 Rocketdyne H-1
Thrust	8,241.763 kN (1,852,822 lbf)
Specific impulse	296 s (2.90 km/s)
Burn time	155 seconds
Fuel	RP-1/LOX
Second stage – S-IVB
Engines	1 Rocketdyne J-2
Thrust	1,031.600 kN (231,913 lbf)
Specific impulse	421 s (4.13 km/s)
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: https://web.archive.org/web/20070521083808/http://www.webcreations.com/ptm.