| 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 (Stage 0) - 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.
Contents |
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.
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.
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