Ariane M
| Function | Super Heavy launch vehicle |
|---|---|
| Manufacturer | N/A |
| Country of origin | Europe |
| Size | |
| Height | 74 m (242 ft) |
| Diameter | ? (?) |
| Mass | 1874,000 kg (4,131,000 lb) |
| Stages | 2/3 |
| Capacity | |
| Payload to LEO | 90,000kg (198,000lb) |
| Payload to GTO | 45,000 kg (99,000lb) |
| Launch history | |
| Status | Not developed |
| Launch sites | ELA-3, Guiana Space Centre |
| Boosters - P230 | |
| No. boosters | 4 |
| Engines | 1 Solid |
| Thrust | 6,470 kN (1,454,510 lbf) |
| Specific impulse | 275 sec |
| Burn time | 129 seconds |
| Fuel | Solid |
| First stage | |
| Engines | 5 Vulcain |
| Thrust | 5,590 kN (1,252,185 lbf) |
| Specific impulse | 430 sec (assumed) |
| Burn time | unknown |
| Fuel | LH2/LOX |
| Second stage | |
| Engines | 1 Vulcain |
| Thrust | 1,114kn (unknown) |
| Specific impulse | 430 sec |
| Burn time | Unknown |
| Fuel | LH2/O2 |
Ariane M is a hypothesized European expendable launch system designed to both place payloads in Low Earth Orbit and loft large payloads to lunar orbit.
History[edit]
The Ariane M was first hypothesized in 1991 as part of a CNES study. However, it was not developed because of prohibitive costs and doubt over its mission requirements.
Future[edit]
In 2001, the ESA established the Aurora programme. This program calls for an eventual human landing on Mars that is targeted for 2030. To achieve such a feat, a heavy launch vehicle is required. Therefore, Ariane M may be required.
References[edit]
External links[edit]
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