Vulcain (rocket engine)

Vulcain

Vulcain 2 engine on display
Country of origin	France  European Union
First flight	1: 4 June 1996 2: 12 February 2005 2.1: 9 July 2024
Last flight	1: 18 December 2009 2: 5 July 2023
Designer	Snecma ArianeGroup
Manufacturer	Snecma ArianeGroup
Application	Main stage engine
Associated LV	1: Ariane 5 G, G+, GS 2: Ariane 5 ECA, ECA+, ES 2.1: Ariane 6
Predecessor	Viking
Status	1: Retired 2: Retired 2.1: In production
Liquid-fuel engine
Propellant	LOX / LH2
Mixture ratio	1: 5.3:1[1] 2: 6.1:1
Cycle	Gas generator
Configuration
Nozzle ratio	1: 45.1:1 2: 58.2:1
Performance
Thrust, vacuum	1: 1,140 kN (260,000 lbf) 2: 1,359 kN (306,000 lbf) 2.1: 1,324 kN (298,000 lbf)
Chamber pressure	1: 100 bar (10,000 kPa) 2: 117.3 bar (11,730 kPa) 2.1: 120.8 bar (12,080 kPa)
Specific impulse, vacuum	1: 431 s (4.23 km/s) 2: 429 s (4.21 km/s)
Dimensions
Length	1: 3.05 m (10.0 ft) 2: 3.44 m (11.3 ft) 2.1: 3.7 m (12 ft)
Diameter	1: 1.76 m (5 ft 9 in) 2: 2.09 m (6 ft 10 in) 2.1: 2.5 m (8 ft 2 in)
Dry mass	1: 1,300 kg (2,900 lb) 2: 1,800 kg (4,000 lb) 2.1: 2,000 kg (4,400 lb)
References
References	[2][3][4][5][6][7][8][9][10]

Vulcain is a family of European first stage rocket engines for Ariane 5 and Ariane 6. Its development began in 1988 and the first flight was completed in 1996. The updated version of the engine, Vulcain 2, was first successfully flown in 2005. Both members of the family use liquid oxygen/liquid hydrogen cryogenic fuel. The new version for Ariane 6 is called Vulcain 2.1.