Saturn-Shuttle
The Saturn-Shuttle was a preliminary concept of launching the Space Shuttle orbiter using a modified version of the first stage of the Saturn V rocket. It was studied and considered in 1971–1972.
NASA model of Saturn-Shuttle configuration | |
| Function | Crewed LEO launch vehicle |
|---|---|
| Manufacturer | Boeing (S-IC) Martin Marietta (External Tank) Rockwell International (Space Shuttle orbiter) |
| Country of origin | United States |
| Size | |
| Height | 86 m (281 ft) |
| Diameter | 10 m (33 ft) |
| Mass | 2,300,000 kg (5,070,000 lb) |
| Stages | 2 |
| Capacity | |
| Payload to LEO | |
| Mass | 60,500 kg (133,400 lb) |
| Launch history | |
| Status | Canceled |
| Launch sites | Kennedy LC-39 |
| First stage – S-IC | |
| Height | 137.99 ft (42.06 m) |
| Diameter | 33 ft (10 m) |
| Empty mass | 298,104 lb (135,218 kg) |
| Gross mass | 5,040,245 lb (2,286,217 kg) |
| Powered by | 5 Rocketdyne F-1 |
| Maximum thrust | 8,700,816 lbf (38,703.16 kN) |
| Specific impulse | 304 seconds (2.98 km/s) |
| Burn time | 161 s |
| Propellant | RP-1/LOX |
| Second stage – External Tank | |
| Height | 153.8 ft (46.9 m) |
| Diameter | 27.5 ft (8.4 m) |
| Empty mass | 65,980 lb (29,930 kg) |
| Gross mass | 1,655,616 lb (750,975 kg) |
| Specific impulse | 455 seconds (4.46 km/s) |
| Burn time | 480 s |
| Propellant | LH2 / LOX |
| Second stage – Orbiter plus External Tank | |
| Powered by | 3 SSMEs located on Orbiter |
| Maximum thrust | 5,250 kN (1,180,000 lbf) |
| Specific impulse | 455 seconds (4.46 km/s) |
| Burn time | 480 s |
| Propellant | LH2 / LOX |
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