HM7B

HM7B
Country of origin	France
First flight	24 December 1979
Designer	Snecma
Manufacturer	Snecma
Application	Upper stage engine
Predecessor	HM4
Successor	Vinci
Status	Retired
Liquid-fuel engine
Propellant	LOX / LH2
Mixture ratio	5:1
Cycle	Gas-generator
Configuration
Chamber	1
Nozzle ratio	83.1:1
Performance
Thrust, vacuum	62.2 kN (13,980 lbf)
Chamber pressure	3.7 MPa (37 bar)
Specific impulse, vacuum	444.6 s (4.36 km/s)
Dimensions
Length	2.01 m (6 ft 7 in)
Diameter	0.992 m (3 ft 3.1 in)
Dry mass	165 kg (364 lb)
Used in
	HM7B: Ariane 5 ECA; Ariane 4; Ariane 3; Ariane 2; HM7(A): Ariane 1;
References
References

The HM7B was a European cryogenic upper stage rocket engine used on the vehicles in the Ariane rocket family.^[3] It was replaced by Vinci, which acts as the new upper stage engine on Ariane 6.^[4] Nearly 300 engines have been produced to date.^[3]

^ ^a ^b B.T.C. Zandbergen. "Simple mass and size estimation relationships of pump fed rocket engines for launch vehicle conceptual design". Retrieved 14 August 2017.
^ Cite error: The named reference AirbusChamber was invoked but never defined (see the help page).
^ ^a ^b ^c Snecma S.A. "HM7B - Snecma". Archived from the original on 2013-04-19. Retrieved 10 August 2014.
^ Safran Group (December 2012). "Safran: Shooting for the StarS" (PDF). Archived from the original (PDF) on 12 August 2014. Retrieved 10 August 2014.