Ariane M

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

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

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

External links

• A .PPT that outlines the Ariane M on its final slides