Atlas III
The Atlas III (known as the Atlas II-AR (R for Russian) early in development ) was an American orbital launch vehicle, used in the years between 2000 and 2005. It was developed from the highly successful Atlas II rocket and shared many components. It was the first member of the Atlas family since the Atlas A to feature a "normal" staging method, compared to the previous Atlas family members, which were equipped with two jettisonable outboard engines on the first (booster) stage (with a single center engine serving as the sustainer). The Atlas III was developed further to create the Atlas V.
The maiden flight of the Atlas III | |
| Function | Medium expendable launch vehicle |
|---|---|
| Manufacturer | Lockheed Martin |
| Country of origin | United States |
| Size | |
| Height | 52.8 m (173 ft) |
| Diameter | 3.05 m (10.0 ft) |
| Mass | 214,338 kg (472,534 lb) |
| Stages | 2 |
| Capacity | |
| Payload to 185 km 28.5° Low Earth orbit | |
| Mass | IIIA: 8,686 kg (19,149 lb) IIIB: 10,759 kg (23,720 lb) |
| Payload to Geostationary transfer orbit | |
| Mass | IIIA: 4,060 kg (8,950 lb) IIIB: 4,500 kg (9,900 lb) |
| Payload to 185 km 90° Polar orbit | |
| Mass | IIIA: 7,162 kg (15,790 lb) IIIB: 9,212 kg (20,309 lb) |
| Associated rockets | |
| Family | Atlas |
| Launch history | |
| Status | Retired |
| Launch sites |
|
| Total launches | 6 (IIIA: 2, IIIB: 4) |
| Success(es) | 6 (IIIA: 2, IIIB: 4) |
| First flight | IIIA: 24 May 2000 IIIB: 21 February 2002 |
| Last flight | IIIA: 13 March 2004 IIIB: 3 February 2005 |
| First stage | |
| Powered by | 1 RD-180 |
| Maximum thrust | 4,148.7 kN (932,700 lbf) |
| Specific impulse | 311 s (3.05 km/s) |
| Burn time | 132 seconds |
| Propellant | RP-1 / LOX |
| Second stage (Atlas IIIA/IIIB) – Centaur (SEC) | |
| Powered by | 1 RL-10A |
| Maximum thrust | 99.2 kN (22,300 lbf) |
| Specific impulse | 451 s (4.42 km/s) |
| Burn time | 738 seconds |
| Propellant | LH2 / LOX |
| Second stage (Atlas IIIB) – Centaur (DEC) | |
| Powered by | 2 RL-10A |
| Maximum thrust | 147 kN (33,000 lbf) |
| Specific impulse | 449 s (4.40 km/s) |
| Burn time | 392 seconds |
| Propellant | LH2 / LOX |
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