Ariane M

Infobox rocket
caption = Ariane M design from a study undretaken by CNES in 1991
name = Ariane M
function = Super Heavy launch vehicle
manufacturer = N/A
country-origin = Europe
height = 74 m
alt-height = 242 ft
diameter = ?
alt-diameter = ?
mass = 1874,000 kg
alt-mass = 4,131,000 lb
stages = 2/3
LEO-payload =90,000kg
alt-LEO =198,000lb
payload-location = GTO
payload = 45,000 kg
alt-payload =99,000lb
status = Not developed
sites = ELA-3, Guiana Space Centre
boosters =4
boostername =P230
boosterengines =1 Solid
boosterthrust =6,470 kN
alt-boosterthrust = 1,454,510 lb_f
boosterSI =275 sec
boostertime =129 seconds
boosterfuel =Solid
stage1
stage1engines = 5 Vulcain
stage1thrust = 5,590 kN
alt-stage1thrust = 1,252,185 lb_f
stage1time = unknown
stage1SI = 430 sec (assumed)
stage1fuel = LH2/LOX
stage2
stage2engines = 1 Vulcain
stage2thrust = 1,114kn
alt-stage2thrust = unknown
stage2time = Unknown
stage2fuel = LH2/O2
stage2SI = 430 sec

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

*http://www.astron.nl/p/news/LO/Iranzo_Ariane5_LOFARworkshop.ppt A PDF that outlines the Ariane M on the final page.