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 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)[1] |
| Payload to Geostationary transfer orbit | |
| Mass | IIIA: 4,060 kg (8,950 lb) IIIB: 4,500 kg (9,900 lb)[1] |
| Payload to 185 km 90° Polar orbit | |
| Mass | IIIA: 7,162 kg (15,790 lb) IIIB: 9,212 kg (20,309 lb)[1] |
| Associated rockets | |
| Family | Atlas |
| Launch history | |
| Status | Retired |
| Launch sites |
|
| Total launches | 6 (IIIA: 2, IIIB: 4) |
| Success(es) | 6 (IIIA: 2, IIIB: 4)[2] |
| 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 |
The Atlas III (known as the Atlas II-AR (R for Russian) early in development [3]) was an American orbital launch vehicle, used in the years between 2000 and 2005.[4] It was developed from the highly successful Atlas II rocket and shared many components.[1] 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.
- ^ a b c d Cite error: The named reference
ppgwas invoked but never defined (see the help page). - ^ "Space Launch Report: Atlas III Data Sheet". 1 December 2005. Archived from the original on 21 March 2022. Retrieved 9 March 2024.
- ^ "Lockheed Martin Selects RD-180 to Power Atlas IIAR". International Launch Services. 17 January 1996. Retrieved 9 March 2013.
- ^ "Atlas IIIA". Encyclopedia Astronautica. Archived from the original on 1 July 2013. Retrieved 8 March 2007.