Ariane M

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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 (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.

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]