Saturn V ELV
| Function | orbital launch vehicle |
|---|---|
| Country of origin | United States |
| Size | |
| Height | 124 m (407 ft) |
| Diameter | 10 m (33 ft) |
| Mass | 5,172,820 kg (11,404,120 lb) |
| Stages | 3 |
| Capacity | |
| Payload to LEO | |
| Mass | 200,000 kg (440,000 lb) |
| Launch history | |
| Status | Proposal |
| Boosters - SRBs | |
| Engines | 4 UA1207 |
| Thrust | 7.12 MN (1,600,000 lbf) |
| Burn time | 120 seconds |
| Propellant | solid |
| First stage - MS-IC-4(S)B | |
| Engines | 5 Rocketdyne F-1 |
| Thrust | 38.72 MN (8,700,000 lbf) |
| Burn time | 206 seconds |
| Propellant | RP-1 / LOX |
| Second stage MS-II-1A | |
| Engines | 7 Rocketdyne J-2 |
| Thrust | 63.81 MN (14,350,000 lbf) |
| Burn time | 625 seconds |
| Propellant | LH2 / LOX |
| Third stage - MS-IVB-1A | |
| Engines | 1 Rocketdyne J-2 |
| Thrust | 1.03 MN (230,000 lbf) |
| Burn time | 625 seconds |
| Propellant | LH2 / LOX |
The Saturn V-ELV (Earth Launch Vehicle) was to be an enlarged Saturn V with the addition of four UA1207 solid rocket boosters derived from the Titan IV launch vehicle and liquid propellant stages derived from the conceptual Saturn MLV-V-4(S)-A* and MLV-V-1A. Had it been built it would have been able to put a 200,000 kg payload into low Earth orbit or a 67,000 kg payload into a translunar trajectory. The ELV was intended to serve as part of a crewed NASA mission to Mars, though that idea eventually fell out of favor largely due to political and financial concerns. A Mars mission would have used a total of 10 ELV's - 6 for the space vehicle and 4 for the logistics vehicles. In addition to Mars, the ELV was intended to serve as a platform for unmanned exploratory missions to Venus.
At the time, it appears ELV was also a generic catch-all term for any large crewed rocket. There are references to both the Saturn I and Saturn V as an ELV.