From Wikipedia, the free encyclopedia
| Saturn IB-D |
| Fact sheet |
| Function |
Unmanned LEO and Lunar launch vehicle |
| Manufacturer |
Von Braun |
| Country of origin |
United States |
| Size |
| Height |
51.00 m (167.00 ft 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 |
| Fuel |
Solid |
| Second Stage - S-1B |
| Engines |
8 Rocketdyne H-1 |
| Thrust |
8,241.763 kN (1,852,822 lbf) |
| Burn time |
155 seconds |
| Fuel |
RP-1/LOX |
| Third Stage - S-IVB |
| Engines |
1 Rocketdyne J-2 |
| Thrust |
1,031.600 kN (231,913 lbf) |
| Burn time |
475 seconds |
| Fuel |
LH2/LOX |
Studied by Douglas 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.
[edit] 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.
