Atlas II
![]() Launch of an Atlas II rocket | |
Function | Medium expendable Launch vehicle |
---|---|
Manufacturer | Lockheed Martin |
Country of origin | United States |
Size | |
Height | 47.54 m (156 ft) |
Diameter | 3.04 m (10 ft) |
Mass | 204,300 kg (414,000 lb) |
Stages | 3.5 |
Capacity | |
Payload to LEO | 6,580 kg |
Payload to GTO |
2,810 kg |
Associated rockets | |
Family | Atlas |
Launch history | |
Status | Retired |
Launch sites | SLC-36, Cape Canaveral SLC-3 Vandenberg AFB |
Total launches | 63 (II: 10, IIA: 23, IIAS: 30) |
Successes | 63 (II: 10, IIA: 23, IIAS: 30)[1] |
First flight | II: 7 December 1991 IIA: 10 June 1992 IIAS: 16 December 1993 |
Last flight | II: 16 March 1998 IIA: 5 December 2002 IIAS: 31 August 2004[1] |
Notable payloads | SOHO (Atlas IIAS) TDRS (Atlas IIA) |
Boosters (Atlas IIAS) - Castor 4A | |
No. boosters | 4 |
Engines | 1 Solid |
Thrust | 478.3 kN (107,530 lbf) |
Specific impulse | 266 sec |
Burn time | 56 seconds |
Fuel | Solid |
Boosters (all) - MA-5 | |
No. boosters | 1 |
Engines | 2 RS-58-OBA |
Thrust | 2,093.3 kN (470,680 lbf) |
Specific impulse | 299 sec |
Burn time | 172 seconds |
Fuel | LOX/RP-1 |
First stage | |
Engines | 1 RS-58-OSA |
Thrust | 386 kN (86,844 lbf) |
Specific impulse | 316 sec |
Burn time | 283 seconds |
Fuel | RP-1/LOX |
Second stage - Centaur | |
Engines | 2 RL-10A |
Thrust | 147 kN (41,592 lbf) |
Specific impulse | 449 sec |
Burn time | 392 seconds |
Fuel | LH2/LOX |
Third stage - IABS (optional) | |
Engines | 1 R-4D |
Thrust | 980N (220 lbf) |
Specific impulse | 312 sec |
Burn time | 60 seconds |
Fuel | N2O4/MMH |
Atlas II was a member of the Atlas family of launch vehicles, which evolved from the successful Atlas missile program of the 1950s. Atlas II was the last Atlas to use a three engine, "stage-and-a-half" design: two of its three engines were jettisoned during ascent, but its fuel tanks and other structural elements were retained. It was designed to launch payloads into low earth orbit, geosynchronous transfer orbit or geosynchronous orbit. Sixty-three launches of the Atlas II, IIA and IIAS models were carried out between 1991 and 2004. (The larger Atlas III was used between 2000 and 2005, and the Atlas V is still in use.)
Features
Atlas II provided higher performance than the earlier Atlas I by using engines with greater thrust and longer fuel tanks for both stages. The total thrust capability of the Atlas II of 490,000 pounds force (2,200 kN) enabled the booster to lift payloads of 6,100 pounds (2,767 kg) into geosynchronous orbit of 22,000 miles (35,000 km) or more. This series used an improved Centaur upper stage – the world’s first high-energy propellant stage – to increase its payload capability. Atlas II also had lower-cost electronics, an improved flight computer and longer propellant tanks than its predecessor, Atlas I.
The most powerful derivative was the Atlas IIAS.
Background
In May 1988, the Air Force chose General Dynamics (now Lockheed-Martin) to develop the Atlas II vehicle, primarily to launch Defense Satellite Communications System payloads and for commercial users as a result of Atlas I launch failures in the late 1980s. Led by lead engineer Samuel Wagner, the Atlas II was crucial to the continued development of the United States' space program.
Atlas IIs were launched from Cape Canaveral Air Force Station, Fla., by the 45th Space Wing. The final West Coast Atlas II launch was accomplished December 2003 by the 30th Space Wing, Vandenberg AFB, Calif.
- General Characteristics[2]
- Primary function: Launch vehicle
- Primary contractor: Lockheed Martin - airframe, assembly, avionics, test and systems integration
- Principal subcontractors: Rocketdyne (Atlas engine, MA-5); Pratt & Whitney (Centaur engine, RL-10) and Honeywell & Teledyne (avionics)
- Power Plant: Three MA-5A (RS-56) Rocketdyne engines, two Pratt & Whitney RL10A-4 Centaur engines
- Thrust: 494,500 lbf (2,200 kN)
- Length: Up to 156 ft (47.54 m); 16 ft (4.87 m) high engine cluster
- Core Diameter: 10 feet (3.04 m)
- Gross Liftoff Weight: 414,000 lb (204,300 kg)
- First Launch: February 10, 1992
- Models: II, IIA, and IIAS
- Launch Site: Cape Canaveral AFS, Florida
- Inventory: unavailable
![](../I/m/Atlas_evolution.png)
See also
References
- ↑ 1.0 1.1 Tariq Malik "Final Atlas 2 Rocket Orbits Classified U.S. Satellite", Space News, August 31, 2004 (Accessed 24 Sept 2014)
- ↑ Spaceflight Now, Atlas IIAS (accessed 24 Sept 2014)
External links
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