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Atlas II  
Initial Operational Capability (IOC): 1991
Total Production: 63
Also Known As: Atlas IIA and Atlas IIAS
Origin: United States of America
Corporations: Lockheed Martin
Parent System: Atlas
Initial Operational Capability (IOC): 1958
Total Production: 587
Family Members: Atlas III and Atlas V
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Description: The Atlas launch vehicle family evolved from successful Atlas intercontinental ballistic missile (ICBM). It is suitable for launch payloads into low earth orbits, geosynchronous transfer orbit (GTO) and geosynchronous orbit. The Atlas launch vehicle family available for military and civil markets currently comprises the Atlas II, Atlas III and Atlas V launch vehicles. Atlas II, III and V provide higher performance than older Atlas I launch vehicle by using engines with greater thrust and longer fuel tanks.

The Atlas II launch vehicle is able to lift payloads of 6,100-lb (2,767 kg) in geosynchronous orbits and 8,200-lb in Geosynchronous Transfer Orbit (GTO). The Centaur high-energy propellant is the upper stage motor of the Atlas II launch vehicle. The Atlas II comprises the Atlas IIA and Atlas IIAS vehicle models. The last Atlas II (#63), an Atlas IIAS, was launched on August 31, 2004, at Cape Canaveral carrying a national security payload into orbit. The Atlas IIAS was introduced in December 1991. Atlas II rocket series ended their service life with 100% success.

Atlas II Specifications

Crew: 0
Height: 48 meter (1,872 inch)
Rocket Diameter: 3.04 meter
Max Lift-off Thrust: 494,500 pound (224 ton)
Max Lift-off Weight: 204 ton (450,485 pound)
Payload to GEO: 6,100 pound (2.77 ton)
Payload to GTO: 8,200 pound (3,720 kilogram)
CEP: Circular Error Probable
Meters (m)   Kilometers (km)   Nautic Miles (nm)   Inch (in)   Yard (yd)   Foot (ft)   Millimeter (mm)
Pound (lb)   Kilogram (kg)   kN (KiloNewton)   Ton (t)
Meters per Second (mps)   Kilometers per Hour (kph)   Knot (kt)   Miles per Hour (mph)
Liter (l)   Galon (gl)
Year (yr)   Minutes (min)   Second (sec)
Shaft-Horse-Power (shp)

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