 | |
| 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)[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]
- ^ 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
AirbusChamberwas 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.