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Space · launch vehicle

Atlas V 551

ULA RETIRED
At a glance
Launches
23
Success rate
100%
23 ok · 0 failed
Payload to LEO
18,850 kg
Payload to GTO
8,890 kg
Status
Retired
First flight
19 Jan 2006
Reusable
No
Height
59.7 m
Diameter
3.8 m
Launch mass
573 t
Liftoff thrust
12,269 kN
Stages
2
Launch cost
$153,000,000
Booster landings
—
About

Atlas V is an expendable launch system in the Atlas rocket family. It was formerly operated by Lockheed Martin and is now operated by United Launch Alliance (ULA), a joint venture with Boeing. Each Atlas V rocket uses a Russian-built RD-180 engine burning kerosene and liquid oxygen to power its first stage and an American-built RL10 engine burning liquid hydrogen and liquid oxygen to power its Centaur upper stage. The RD-180 engines are provided by RD Amross, while Aerojet Rocketdyne provides both the RL10 engines and the strap-on boosters used in some configurations. The standard payload fairing sizes are 4 or 5 meters in diameter and of various lengths. Fairings sizes as large as 7.2 m in diameter and up to 32.3 m in length have been considered. The rocket is assembled in Decatur, Alabama and Harlingen, Texas.