Atlas V

Atlas V is an expendable launch system and the fifth major version in the Atlas launch vehicle family. It was originally designed by Lockheed Martin, now being operated by United Launch Alliance (ULA), a joint venture between Lockheed Martin and Boeing. It is used for DoD, NASA, and Commercial payloads. It is America's longest-serving active rocket. After 87 launches, in August 2021 ULA announced that Atlas V would be retired, and all 29 remaining launches had been sold. As of January 2024, 17 launches remain. Other future ULA launches will use the new Vulcan Centaur rocket.

This article is about the rocket. For the boat, see Atlas V (tugboat).

Atlas V
Launch of an Atlas V 401 carrying the Lunar Reconnaissance Orbiter and LCROSS space probes on 18 June 2009.
Function
ManufacturerUnited Launch Alliance
Country of originUnited States
Cost per launchUS$110–153 million in 2016
Size
Height58.3 m (191 ft) with payload fairing, 52.4 m (172 ft) with Starliner
Diameter3.81 m (12.5 ft)
Mass590,000 kg (1,300,000 lb)
Stages2
Capacity
Payload to low Earth orbit
Orbital inclination28.70°
Mass8,210–18,850 kg (18,100–41,560 lb)
Payload to geostationary transfer orbit
Mass4,750–8,900 kg (10,470–19,620 lb)
Associated rockets
FamilyAtlas
Based onAtlas III
Comparable
Launch history
StatusActive
Launch sites
Total launches
99
  • 401: 41
  • 411: 6
  • 421: 9
  • 431: 3
  • 501: 8
  • 511: 1
  • 521: 2
  • 531: 5
  • 541: 9
  • 551: 13
  • N22: 2
Success(es)
98
  • 401: 40
  • 411: 6
  • 421: 9
  • 431: 3
  • 501: 8
  • 511: 1
  • 521: 2
  • 531: 5
  • 541: 9
  • 551: 13
  • N22: 2
Partial failure(s)15 June 2007
First flight21 August 2002
Hot Bird 6
Last flight6 October 2023
Project Kuiper 2-satellite test
Type of passengers/cargo
Boosters – AJ-60A
No. boosters0 to 5
Height17 m (56 ft)
Diameter1.6 m (5 ft 3 in)
Gross mass46,697 kg (102,949 lb)
Propellant mass42,630 kg (93,980 lb)
Maximum thrust1,688.4 kN (379,600 lbf)
Specific impulse279.3 s (2.739 km/s)
Burn time94 seconds
PropellantHTPB
Boosters – GEM 63
No. boosters0 to 5
Height20.1 m (66 ft)
Diameter1.6 m (5 ft 3 in)
Gross mass49,300 kg (108,700 lb)
Propellant mass44,200 kg (97,400 lb)
Maximum thrust1,663 kN (374,000 lbf)
Burn time94 seconds
PropellantHTPB
First stage – Atlas CCB
Height32.46 m (106.5 ft)
Diameter3.81 m (12.5 ft)
Empty mass21,054 kg (46,416 lb)
Propellant mass284,089 kg (626,309 lb)
Powered by1 RD-180
Maximum thrust
  • 3,827 kN (860,000 lbf) (sea level)
  • 4,152 kN (933,000 lbf) (vacuum)
Specific impulse
  • 311.3 s (3.053 km/s) (sea level)
  • 337.8 s (3.313 km/s) (vacuum)
Burn time253 seconds
PropellantRP-1 / LOX
Second stage – Centaur
Height12.68 m (41.6 ft)
Diameter3.05 m (10.0 ft)
Empty mass2,316 kg (5,106 lb)
Propellant mass20,830 kg (45,920 lb)
Powered by1 RL10A or 1 RL10C (SEC), or 2 RL10A (DEC)
Maximum thrust99.2 kN (22,300 lbf) (RL10A)
Specific impulse450.5 s (4.418 km/s) (RL10A-4-2)
Burn time842 seconds (RL10A-4-2)
PropellantLH2 / LOX

Each Atlas V launch vehicle consists of two main stages. The first stage is powered by a Russian RD-180 engine manufactured by Energomash and burning kerosene and liquid oxygen. The Centaur upper stage is powered by one or two American RL10 engine(s) manufactured by Aerojet Rocketdyne and burns liquid hydrogen and liquid oxygen. Strap-on solid rocket boosters (SRBs) are used in most configurations. AJ-60A SRBs were used originally, but they were replaced in November 2020 by Graphite-Epoxy Motor (GEM 63) SRBs. The standard payload fairings are 4.2 or 5.4 m (14 or 18 ft) in diameter with various lengths.

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