Atlas I
Launch of the maiden flight of the Atlas I, with the CRRES satellite | |
| Function | Expendable launch system |
|---|---|
| Manufacturer | General Dynamics |
| Country of origin | United States |
| Size | |
| Height | 43.90m (144.00 ft) |
| Diameter | 3.05m (10 ft) |
| Mass | 164,300kg (362,200 lb) |
| Stages | 2.5 |
| Capacity | |
| Payload to 185 km (115 mi) LEO | |
| Mass | 5,900 kg (13,000 lb) |
| Payload to GTO | |
| Mass | 2,375 kg (5,236 lb) |
| Associated rockets | |
| Family | Atlas |
| Launch history | |
| Status | Retired |
| Launch sites | LC-36B, Cape Canaveral |
| Total launches | 11 |
| Success(es) | 8 |
| Failure(s) | 3 |
| First flight | July 25, 1990 |
| Last flight | April 25, 1997 |
| Boosters – MA-5 | |
| No. boosters | 1 |
| Powered by | 2 LR-89-7 |
| Maximum thrust | 1,901.6 kN (427,500 lbf) |
| Specific impulse | 293.4 s (2.877 km/s) |
| Burn time | 155 seconds |
| Propellant | RP-1 / LOX |
| First stage | |
| Powered by | 1 LR-105-7 |
| Maximum thrust | 386.4 kN (86,900 lbf) |
| Specific impulse | 316 s (3.10 km/s) |
| Burn time | 266 seconds |
| Propellant | RP-1 / LOX |
| Second stage – Centaur | |
| Powered by | 2 RL-10A |
| Maximum thrust | 147 kN (33,000 lbf) |
| Specific impulse | 449 s (4.40 km/s) |
| Burn time | 410 seconds |
| Propellant | LH2 / LOX |
The Atlas I was a US expendable launch system manufactured by General Dynamics in the 1990s to launch a variety of satellites. It was largely a commercial rebrand of the Atlas G (although it did fly multiple government payloads), but did feature several electrical and guidance improvements. Atlas I did not feature any major payload capacity improvements over its predecessor but did offer a larger payload fairing option. Eleven launches took place, with three failures.
Atlas I would be further developed and improved upon to produce the highly successful Atlas II rocket.