Launch vehicles

Airman, Jan, 2005

Atlas II Primary function: Space launch vehicle Dimensions: Core diameter, 10 feet; Length, up to 156 feet, engine cluster hight 16 ft. Payload capability: 6,100 pounds in geosynchronous orbit.

Delta II Primary function: Space-lift vehicle. Dimensions: Length 125 ft. 9 in., diameter 8 ft. Payload: Navstar Global Positioning System, as well as civil and commercial satellites into low earth, polar, geotransfer and geosynchronous orbits.

Titan IVB Primary function: Space-lift vehicle. Dimensions: Inertial upper stage length 17 ft., diameter flares from 7 ft. 6 in. to 9 ft. 6 in. First stage length 86 ft. 6 in., diameter 10 ft. Second stage length 32 ft. 8 in., diameter 10 ft. Payload capability: up to 47,800 lbs. into low-earth orbit; up to 12,700 lbs. into geosynchronous orbit when launched from Cape Canaveral Air Station, Fla., and up to 38,000 lbs. into a low-earth polar orbit when launched from Vandenberg AFB, Calif. Using an inertial upper stage, up to 5,250 lbs. into geosynchronous orbit.

Atlas V Primary function: Evolved expendable launch vehicle designed to improve space launch operability and standardization. Dimensions: Three common core boosters, each booster diameter 12 ft. 6 in. Payload capability: 42,000 lbs. into low earth orbit; 29,000 lbs. into geotransfer orbit; 14,000 lbs. into geostationary orbit.

Delta IV Primary function: Evolved expendable launch vehicle designed to improve space launch operability and standardization. Dimensions: Common core booster length 205 ft., diameter 16 ft. 8 in. Payload capability: 17,900 lbs. into low earth orbit; 9,285 lbs. into geotransfer orbit.

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