 | |
| Function | Uncrewed launch vehicle |
|---|---|
| Manufacturer | Von Braun |
| Country of origin | United States |
| Size | |
| Height | 62 m (203.00 ft) |
| Diameter | 6.52 m (21.39 ft) |
| Mass | 524,484 kg |
| Stages | 3 (all used on various vehicles, now retired) |
| Capacity | |
| Payload to LEO | 10,000 kg |
| Launch history | |
| Status | Never flown |
| Launch sites | N/A |
| First stage - S-IB | |
| Engines | 8 × Rocketdyne H-1 |
| Thrust | 1,600,000 lbf (7,100 kN) |
| Burn time | 150 seconds |
| Propellant | RP-1/LOX |
| Second stage Jupiter Cluster | |
| Engines | 4 x Rocketdyne LR79 |
| Thrust | 3,034.285 kN |
| Burn time | 172 seconds |
| Propellant | RP-1/LOX |
| Third stage - Centaur C | |
| Engines | 2 RL10A-1 |
| Thrust | 133 kN |
| Burn time | 430 seconds |
| Propellant | LH2 |
Studied with the Saturn A-1 in 1959, the Saturn A-2 was deemed more powerful than the Saturn I rocket. It was proposed as a launcher for Project Horizon, a scientific / military base on the Moon project, at a time when the U.S. Department of the Army, Department of the Navy, and Department of the Air Force had total responsibility for U.S. space program plans.
The rocket consisting of a S-IB first stage with eight H-1 engines (which actually flew on the Saturn IB), a Jupiter Cluster second stage equipped which four LR79 engines (used on the Jupiter IRBM) and a Centaur C high-energy liquid-fueled third stage with a double RL10A-1 engine.
