Atlas V

Launch of an Atlas V 401 carrying the LRO and LCROSS
Function	EELV/Medium-heavy launch vehicle
Manufacturer	United Launch Alliance
Country of origin	United States
Size
Height	58.3 meters (191 ft)
Diameter	3.81 meters (12.5 ft)
Mass	334,500 kilograms (737,400 lb)
Stages	2
Capacity
Payload to LEO	9,800–18,810 kilograms (21,610–41,470 lb)
Payload to GTO	4,750–8,900 kilograms (10,470–19,620 lb)
Associated rockets
Comparable	Delta IV, Falcon 9 FT
Launch history
Status	Active
Launch sites	Cape Canaveral SLC-41 Vandenberg SLC-3E
Total launches	69 (401: 34, 411: 4, 421: 6, 431: 3) (501: 6, 521: 2, 531: 3, 541: 4, 551: 7)
Successes	68 (401: 33, 411: 4, 421: 6, 431: 3) (501: 6, 521: 2, 531: 3, 541: 4, 551: 7)
Partial failures	1 (401)
First flight	401: 21 August 2002 411: 20 April 2006 421: 10 October 2007 431: 11 March 2005 501: 22 April 2010 521: 17 July 2003 531: 14 August 2010 541: 26 November 2011 551: 19 January 2006
Last flight	401: 21 January 2017 (SBIRS-GEO-3) 411: 09 September 2016 (OSIRS-REx) 421: 28 July 2016 (NROL-61) 431: 18 December 2016 (EchoStar-19) 501: 20 May 2015 (AFSPC-5) 521: 17 December 2004 (AMC-16) 531: 18 September 2013 (AEHF-3) 541: 19 November 2016 (GOES-R) 551: 24 June 2016 (MUOS-5)
Notable payloads	Mars Reconnaissance Orbiter New Horizons LRO/LCROSS Solar Dynamics Observatory Boeing X-37B Juno Mars Science Laboratory OSIRIS-REx
Boosters - AJ-60A
No. boosters	0 to 5
Length	17.0 m (669 in)
Diameter	1.6 m (62 in)
Gross mass	46,697 kg (102,949 lb)
Thrust	1,688.4 kN (379,600 lbf)
Specific impulse	279.3 seconds (2.739 km/s)
Burn time	94 seconds
Fuel	HTPB
Boosters (Heavy, cancelled) - Atlas CCB
No. boosters	2
Length	32.46 m (106.5 ft)
Diameter	3.81 m (12.5 ft)
Empty mass	23,648 kg (52,135 lb)
Propellant mass	286,795 kg (632,275 lb)
Engines	1 RD-180
Thrust	3,827 kN (860,000 lbf) (SL) 4,152 kN (933,000 lbf) (Vac)
Specific impulse	311.3 seconds (3.053 km/s) (SL) 337.8 seconds (3.313 km/s) (Vac)
Burn time	253 seconds
Fuel	RP-1/LOX
First stage - Atlas CCB
Length	32.46 m (106.5 ft)
Diameter	3.81 m (12.5 ft)
Empty mass	21,054 kg (46,416 lb)
Propellant mass	284,089 kg (626,309 lb)
Engines	1 RD-180
Thrust	3,827 kN (860,000 lbf) (SL) 4,152 kN (933,000 lbf) (Vac)
Specific impulse	311.3 seconds (3.053 km/s) (SL) 337.8 seconds (3.313 km/s) (Vac)
Burn time	253 seconds
Fuel	RP-1/LOX
Second stage - Centaur
Length	12.68 m (41.6 ft)
Diameter	3.05 m (10.0 ft)
Empty mass	2,316 kg (5,106 lb)
Propellant mass	20,830 kg (45,920 lb)
Engines	1 RL10A or 1 RL10C
Thrust	99.2 kN (22,300 lbf) (RL10A)
Specific impulse	450.5 seconds (4.418 km/s) (RL10A-4-2)
Burn time	842 seconds (RL10A-4-2)
Fuel	LH2/LOX

Atlas V is an active expendable launch system in the Atlas rocket family. Atlas V was formerly operated by Lockheed Martin, and is now operated by the Lockheed Martin-Boeing joint venture United Launch Alliance (ULA). 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.

The Atlas V was developed by Lockheed Martin Commercial Launch Services as part of the US Air Force Evolved Expendable Launch Vehicle (EELV) program and made its inaugural flight on August 21, 2002. The vehicle operates out of Space Launch Complex 41 at Cape Canaveral Air Force Station and Space Launch Complex 3-E at Vandenberg Air Force Base. Lockheed Martin Commercial Launch Services continues to market the Atlas V to commercial customers worldwide.