| Function | Launch vehicle for Project Horizon and Apollo |
|---|---|
| Country of origin | United States |
| Size | |
| Height | 224.6 feet (68.5 m) (w/o payload) |
| Diameter | 21.4 feet (6.5 m) |
| Mass | 1,367,000 pounds (620,000 kg) gross (to LEO) |
| Capacity | |
| Payload to LEO | |
| Mass | 47,300 pounds (21,500 kg) |
| Payload to Moon | |
| Mass | 14,900 pounds (6,800 kg) |
| Associated rockets | |
| Family | Saturn |
| Launch history | |
| Status | Study, not developed |
| Launch sites | Kennedy Space Center |
| First stage – S-I | |
| Height | 80.3 feet (24.5 m) |
| Diameter | 21.4 feet (6.5 m) |
| Empty mass | 99,800 pounds (45,300 kg) |
| Gross mass | 953,900 pounds (432,700 kg) |
| Powered by | 8 H-1 |
| Maximum thrust | 1,500,000 pounds-force (6,700 kN) |
| Specific impulse | 289 secs |
| Burn time | 150 seconds |
| Propellant | RP-1 / LOX |
| Second stage – S-II[1] | |
| Height | 74.0 feet (22.6 m) |
| Diameter | 21.6 feet (6.6 m) |
| Empty mass | 30,000 pounds (14,000 kg) |
| Gross mass | 220,000 pounds (100,000 kg) |
| Powered by | 4 J-2 |
| Maximum thrust | 800,000 pounds-force (3,600 kN) |
| Specific impulse | 300 sec |
| Burn time | 100 seconds |
| Propellant | LH2 / LOX |
| Third stage – S-IV | |
| Height | 40.0 feet (12.2 m) |
| Diameter | 18.0 feet (5.5 m) |
| Empty mass | 11,500 pounds (5,200 kg) |
| Gross mass | 111,500 pounds (50,600 kg) |
| Powered by | 6 RL10 |
| Maximum thrust | 90,000 pounds-force (400 kN) |
| Specific impulse | 410 secs |
| Burn time | 482 seconds |
| Propellant | LH2 / LOX |
| Fourth stage – S-V (Centaur-C) | |
| Height | 30.0 feet (9.1 m) |
| Diameter | 10.0 feet (3.0 m) |
| Empty mass | 4,400 pounds (2,000 kg) |
| Gross mass | 34,300 pounds (15,600 kg) |
| Powered by | 2 RL10 |
| Maximum thrust | 30,000 pounds-force (130 kN) |
| Specific impulse | 410 secs |
| Burn time | 430 seconds |
| Propellant | LH2 / LOX |
The Saturn C-2 was the second rocket in the Saturn C series studied from 1959 to 1962. The design was for a four-stage launch vehicle that could launch 21,500 kg (47,300 lb) to low Earth orbit and send 6,800 kg (14,900 lb) to the Moon via Trans-Lunar Injection.[2]
The C-2 design concept was for a proposed crewed circumlunar flight and the Earth orbit rendezvous (EOR) missions. It was initially considered for the Apollo lunar landing at the earliest possible date (1967).