Atlas II
Atlas II
Space Launch Systems
Basic Information
Name
Atlas II
Designation
Atlas II
Alternate Designation
Atlas IIA, Atlas IIAS
Equipment Type
Space Launch Systems
Manufacturer
Lockheed Martin
Date of Introduction
1991
Description
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.
Overview (Deagel)
Group
Space Launch Systems
Status
Retired - No Longer Operational
Also Known As
Atlas IIA, Atlas IIAS
Origin
United States of America
Contractor
Lockheed Martin
Initial Operational Capability (IOC)
1991
Total Production
63
Specifications (Deagel)
Crew
0
Dimensions — Height
47.5 meter
Dimensions — Rocket Diameter
3.0 meter
Mass — Max Lift-off Thrust
494,500 pound
Mass — Max Lift-off Weight
204 ton
Mass — Payload to GEO
6,100 pound
Mass — Payload to GTO
8,200 pound
Variants
Variant 1
Atlas II
Variant 2
Atlas III
Variant 3
Atlas V
Details
Country of Origin
United States
Sources
deagel.com: https://www.deagel.com/x/x/a000237
Classification
Domain
Air & Air Defense
Equipment Status
Active
Dimensions
Length
—
Width
3 m
Height
47.5 m
Weight
204000 kg
Operators (1)
United States
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