![]() 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)[1] |
Payload to GTO | |
Mass | 2,375 kg (5,236 lb)[2] |
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[3] | |
No. boosters | 1 |
Powered by | 2 LR-89-7 |
Maximum thrust | 1,901.6 kN (427,500 lbf)[3] |
Specific impulse | 293.4 s (2.877 km/s) |
Burn time | 155 seconds[2] |
Propellant | RP-1 / LOX |
First stage | |
Powered by | 1 LR-105-7 |
Maximum thrust | 386.4 kN (86,900 lbf)[3] |
Specific impulse | 316 s (3.10 km/s) |
Burn time | 266 seconds[2] |
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[2] |
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.[4] Atlas I did not feature any major payload capacity improvements over its predecessor[1] but did offer a larger payload fairing option.[2] Eleven launches took place, with three failures.
Atlas I would be further developed and improved upon to produce the highly successful Atlas II rocket.[2]