Draft:Saturn INT-12
| Function | Launch vehicle for Apollo |
|---|---|
| Country of origin | United States |
| Size | |
| Height | 167 feet (51 m) (w/o payload) |
| Diameter | 21.68 feet (6.61 m) |
| Mass | 3,327,280 pounds (1,509,230 kg) gross (to LEO) |
| Capacity | |
| Payload to LEO | |
| Mass | 74,000 pounds (34,000 kg) |
| Associated rockets | |
| Family | Saturn |
| Launch history | |
| Status | Study, not developed |
| Launch sites | Kennedy Space Center |
| Zero stage – Solid Rocket Boosters | |
| Height | 85 feet (26 m) |
| Diameter | 10 feet (3.0 m) |
| Empty mass | 74,511 pounds (33,798 kg) |
| Gross mass | 498,758 pounds (226,233 kg) |
| Powered by | 4 UA1205 |
| Maximum thrust | 1,315,000 pounds-force (5,850 kN) |
| Specific impulse | 238 secs |
| Burn time | 115 seconds |
| Propellant | APCP |
| First stage – S-IB-4 | |
| Height | 80.31 feet (24.48 m) |
| Diameter | 21.39 feet (6.52 m) |
| Empty mass | 82,800 pounds (37,600 kg) |
| Gross mass | 980,300 pounds (444,700 kg) |
| Powered by | 4 H-1 |
| Maximum thrust | 926,370 pounds-force (4,120.7 kN) |
| Specific impulse | 296 secs |
| Burn time | 282 seconds |
| Propellant | Kerosene / LOX |
| Second stage – S-IVB | |
| Height | 58.3 feet (17.8 m) |
| Diameter | 21.68 feet (6.61 m) |
| Empty mass | 28,400 pounds (12,900 kg) |
| Gross mass | 261,900 pounds (118,800 kg) |
| Powered by | 1 J-2 |
| Maximum thrust | 231,913 pounds-force (1,031.60 kN) |
| Burn time | 475 seconds |
| Propellant | LH2 / LOX |
The Saturn INT-12 was an unflown member of the Saturn family of launch vehicles. It was conceptualized as a variant of the Saturn IB, with the S-IB first stage only having four engines instead of the usual eight, and four UA1205 solid rocket motors being attached to the side.
See also
References
- Bibliography
Encyclopedia Astronautica Saturn INT-12
| Early proposals |  | |
|---|---|---|
| "C" series | ||
| Saturn I series | ||
| Saturn II series | ||
| Saturn V series | ||