![]() | |
Country of origin | ![]() |
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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)[1] |
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 | |
References | |
References | [1][2][3] |
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]
AirbusChamber
was invoked but never defined (see the help page).