| Stage 0 (Solid Rocket Motor Upgrade) |
Length | 112.4 feet |
|
|
Diameter | 10.5 feet | |
|
Motor Thrust | 1.7 million lb. per motor | |
Weight | 777,000 pounds | |
Contractor | Alliant Techsystems |
| | |
| First Stage |
Length | 86.5 feet |
|
|
Diameter | 10 feet | |
|
Thrust | 551,200 lbs. (full duration average) | |
|
Contractor | Lockheed Martin Astronautics |
| | |
| Second Stage |
Length | 32.7 feet (bottom of engine nozzle
to top of forward skirt) |
|
|
Diameter | 10 feet | |
|
Thrust | 106,150 lbs. (full duration average) | |
|
Contractor | Lockheed Martin Astronautics |
| | |
| Centaur Upper Stage |
Length | 29.4 feet |
|
|
Diameter | 170 inches | |
|
Thrust | 33,000 lbs. | |
|
Contractor | Lockheed Martin Astronautics |
| | |
| Inertial Upper Stage |
Length | 17 feet |
|
|
Diameter | 114 inches | |
|
Thrust | 41,700 lbs./17,200 lbs. (average thrust) | |
|
Contractor | Boeing Defense and Space Group |
