Vega (launcher)

Infobox rocket

---

caption = Vega rocket
imsize=100px
name = Vega
function = Small orbital launch vehicle
manufacturer = ESA/ASI
country-origin = Europe
height = 30 m
alt-height =
diameter = 3 m
alt-diameter =
mass = 137,000 kg
alt-mass =
stages = 4
LEO-payload =1,500 kg
alt-LEO =
status = In Development
sites = ZLV (ELA-1), Centre Spatial Guyanais
first=Planned for 2009
last=
stage1engines = 1 P80
stage1thrust = 3040 kN
alt-stage1thrust =
stage1time = 107 seconds
stage1fuel = Solid
stage2engines = 1 Zefiro 23
stage2thrust = 1200 kN
alt-stage2thrust =
stage2time = 71.6 seconds
stage2fuel = Solid
stage3engines = 1 Zefiro 9
stage3thrust = 213 kN
alt-stage3thrust =
stage3time = 117 seconds
stage3fuel = Solid
stage4engines = 1 AVUM
stage4thrust = 2.45 kN
alt-stage4thrust =
stage4time = 315.2 seconds
stage4fuel = UDMH/N2O4

Vega ("Vettore Europeo di Generazione Avanzata" [ESA: Antonio Fabrizi: from 'nuts and bolts' to Europe’s launchers of today and tomorrow [http://www.esa.int/SPECIALS/Space_Year_2007/SEMFRSQ08ZE_0.html] ] , European Advanced Generation Carrier [Rocket] ) is a planned expendable launch system developed for Arianespace jointly by the Italian Space Agency and the European Space Agency since 1998, with the first launch planned for 2009.

It is designed to launch small payloads: 300 to 2,000 kg satellites for scientific and Earth observation missions to polar and low earth orbits. It is named after the star Vega. It is a single body launcher with three solid rocket stages, the P80 first stage, the Zefiro23 second stage, the Zefiro9 third stage, and a liquid rocket upper module called AVUM.

The technology developed for the "P80 program" shall also be used for future Ariane developments. Italy is the leading contributor to the Vega program with 65%, other participants being France (12.43%), Belgium (5.63%), Spain (5%), The Netherlands (3.5%), Switzerland (1.34%) and Sweden (0.8%).

The reference VEGA mission is a polar orbit bringing a spacecraft of 1,500 kilograms to an altitude of 700 kilometers.

Engine tests

Each of the three engine types intended for the three stages of the Vega had to be commissioned with two test-firings: one for design evaluation, one in final flight configuration.

Zefiro 9

The first engine completed was Zefiro 9, the third stage engine. The first test firing was carried out on 20 December 2005, at the Salto di Quirra Inter-force Test Range, on the Mediterranean coast in southeast Sardinia. The test was a complete success. [ESA: Successful first test for Vega's Zefiro 9 engine [http://www.esa.int/esaCP/SEMNL68A9HE_index_0.html] ]

After a critical design review based on the completed first test firings [ESA: Vega Critical Design Review begins [http://www.esa.int/SPECIALS/Launchers_Home/SEMGM4SVYVE_0.html] ] , on 28 March 2007, the second test-firing of the Zefiro 9 took place at Salto di Quirra. After 35 seconds, there was a sudden drop in the motor's internal pressure, leading to an increased combustion time. [ESA: Anomalous behaviour affects firing test of Vega’s Zefiro 9 motor [http://www.esa.int/esaCP/SEMCVFT4LZE_index_0.html] ]

Zefiro 23

The Zefiro 23 second stage engine was first fired on 26 June 2006 at Salto di Quirra. This test was successful, too. [ESA: Vega's second stage motor roars to life [http://www.esa.int/esaCP/SEMH4REFWOE_Expanding_0.html] ]

The second test firing of the Zefiro 23 second stage engine took place on 27 March 2008 also at Salto di Quirra. This test was concluded successfully again which qualified the rocket engine. [http://www.esa.int/esaCP/SEMSEBR03EF_index_0.html Successful qualification firing test for Zefiro 23]

P80

The first test firing of the P80 first stage engine took place on 30 November 2006 in Kourou, and the test was concluded successfully. [ESA: Successful firing of Vega’s first-stage motor in Kourou [http://www.esa.int/SPECIALS/Launchers_Home/SEMTHGD4VUE_0.html] ]

The second test firing of the P80 first stage engine took place on 4 December 2007 in Kourou. Delivering a mean thrust of 190 tonnes over 111 seconds, the engine's behaviour was in line with predictions. [ESA: Vega main engine test in Kourou [http://www.esa.int/SPECIALS/Launchers_Home/SEMXE029R9F_0.html] ]

Future developments

The future upgraded Vega ("LYRA program") has exceeded the feasibility study and is planned to have new third and fourth low cost LOX/HC stages and a new guidance system. The purpose of the program is to upgrade the polar orbit payloads to up 2,000 kg.

References

External links

* [http://www.esa.int/SPECIALS/Launchers_Access_to_Space/SEMH3E67ESD_0.html Vega launcher] , European Space Agency.
* [http://www.esa.int/esaCP/SEM4AU0A90E_index_0.html First stone for Vega at Europe's Spaceport]
* [http://esamultimedia.esa.int/docs/VEGAbrochure.pdf Vega brochure]
* [http://www.esa.int/esapub/bulletin/bulletin128/bul128_inbrief.pdf Vega Nozzle]