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Vega (rocket)

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Vega
Vega rocket
FunctionSmall orbital launch vehicle
ManufacturerESA/ASI
Country of originEurope
Size
Height30 m
Diameter3 m
Mass137,000 kg
Stages4
Capacity
Payload to LEO1,500 kg
Launch history
StatusIn Development
Launch sitesZLV (ELA-1), Centre Spatial Guyanais
First flightPlanned for 2010
First stage
Engines1 P80
Thrust3040 kN
Burn time107 seconds
PropellantSolid
Second stage
Engines1 Zefiro 23
Thrust1200 kN
Burn time71.6 seconds
PropellantSolid
Third stage
Engines1 Zefiro 9
Thrust213 kN
Burn time117 seconds
PropellantSolid
Fourth stage
Engines1 AVUM
Thrust2.45 kN
Burn time315.2 seconds
PropellantUDMH/N2O4
[edit on Wikidata]

Vega (Vettore Europeo di Generazione Avanzata[1], European Advanced Generation Carrier [Rocket]) is an expendable launch system being developed for Arianespace jointly by the Italian Space Agency and the European Space Agency. Development began in 1998 and the first launch, which will take place from the Guiana Space Centre, is planned for November 2010. It is named from the star Vega.

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.[citation needed] The reference Vega mission is a polar orbit bringing a spacecraft of 1,500 kilograms to an altitude of 700 kilometers.

Vega is a single-body launcher (no strap-on boosters) with three solid rocket stages, the P80 first stage, the Zefiro 23 second stage, the Zefiro 9 third stage, and a liquid rocket upper module called AVUM. The technology developed for the P80 program will also be used for future Ariane developments. Italy is the leading contributor to the Vega program with 65%; other participants include France (12.43%), Belgium (5.63%), Spain (5%), The Netherlands (3.5%), Switzerland (1.34%) and Sweden (0.8%).

Payload capacity

Arianespace indicates a Vega launcher will be able to carry 1,500 kilograms (3,300 lb) to a circular polar orbit at an altitude of 700 kilometres (430 mi).[2] Arianespace is marketing Vega as a launch system tailored for missions to low Earth and sun-synchronous orbits.[3]

Solid motor stages

The first three stages are solid motors produced by AVIO.[citation needed]

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.[4]

After a critical design review based on the completed first test firings[5], 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.[6] No public information is available for this sudden drop of internal pressure, and what if any flaws were present in the motor's design.

On 23 October 2008 an enhanced version of the Zefiro 9 with a modified nozzle design, the Zefiro 9-A, was successfully tested.[7]

On 28 April, the final qualification test firing of Zefiro 9-A took place at the Salto di Quirra Interforce Test Range in Sardinia, Italy.[8]

Zefiro 23

The development of the Zefiro motor was initiated by FiatAvio, partially funded by the company and partially funded by a contract from the Italian Space Agency. A Zefiro 23 forms the second stage of Vega. Its carbon-epoxy case is filament-wound and its carbon phenolic nozzle includes a carbon-carbon throat insert. The propellant loading is 23 tons.[9]

The Zefiro 23 second stage engine was first fired on 26 June 2006 at Salto di Quirra. This test was successful, too.[10]

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.[11]

P80

The P80 first stage also uses a filament-wound case. Its nozzle uses a flexible joint that is electrically actuated.[9]

The first test firing of the P80 engine took place on 30 November 2006 in Kourou, and the test was concluded successfully.[12]

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.[13]

AVUM upper stage

The AVUM (Attitude Vernier Upper Module) stage consists of a propulsion module and an avionics module. The planned propulsion module uses a liquid-fuel rocket burning pressure-fed UDMH and nitrogen tetroxide as propellants. A cold nitrogen gas system provides attitude control.[14] The AVUM avionics module contains the main components of the avionics sub-system of the vehicle.

Planned flights

The first launch of the system is due in November 2010. [15] [16]

After this qualification flight, ESA plans for a second flight, followed by four more flights in its "VERTA programme."[17]

Enrico Saggesse, the new head of the Italian Space Agency suggested in October 2008 that the first flight of VEGA might be delayed, stating "We have to decide if we want to wait until we have another programme", and referring to plans to have German participation to develop new third and fourth stages. [18]

The Italian Aerospace Research Centre plans to launch its "FTB-X" test vehicle on a Vega launcher in 2012.[19]

Future developments

There was a concept study for a new medium-size launcher based on Vega and Ariane 5 elements. This launcher would use an Ariane 5 P230 first stage, a Vega P80 second stage and an Ariane 5 third stage using either storable or cryogenic fuel.[9] The addition of Soyuz to the Arianespace launch vehicle lineup removed momentum from this initiative.

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 to 2,000 kg.

Stages

First Stage Second Stage Third Stage Fourth Stage
Propulsion P80 Zefiro 23 Zefiro 9 AVUM
Height 10.5 m 7.5 m 3.85 m 1.74 m
Diameter 3 m 1.9 m 1.9 m 1.9 m
Propellant mass 88 t 23.9 t 10.1 t 0.55 t
Thrust (max) 3,040 kN 1,200 kN 213 kN 2.45 kN
Nozzle expansion ratio 16 25 56 -
Burn time 107 s 71.6 s 117 s 315.2 s

See also

References

  1. ^ ESA: Antonio Fabrizi: from 'nuts and bolts' to Europe’s launchers of today and tomorrow [1]
  2. ^ "Vega - Overview". Arianespace.
  3. ^ "Vega - Performance". Arianespace.
  4. ^ ESA: Successful first test for Vega's Zefiro 9 engine [2]
  5. ^ ESA: Vega Critical Design Review begins [3]
  6. ^ ESA: Anomalous behaviour affects firing test of Vega’s Zefiro 9 motor [4]
  7. ^ "Successful first test for Vega's Zefiro 9-A solid-fuel rocket motor". ESA. 24 October 2008.
  8. ^ "Successful second test for Vega's Zefiro 9-A solid-fuel rocket motor". ESA. 30 April 2009.
  9. ^ a b c M. Caporicci (November 2000). "The Future of European Launchers: The ESA Perspective" (PDF). ESA.
  10. ^ ESA: Vega's second stage motor roars to life [5]
  11. ^ http://www.esa.int/esaCP/SEMSEBR03EF_index_0.html Successful qualification firing test for Zefiro 23
  12. ^ ESA: Successful firing of Vega’s first-stage motor in Kourou [6]
  13. ^ ESA: Vega main engine test in Kourou [7]
  14. ^ "AVUM". AVIO.
  15. ^ "Avio: Vega's motors qualify but maiden launch slips to 2010". flightglobal.com. 29 April 2009.
  16. ^ "Delays seen for Souuz, VEGA launches at Europe's Space Base". AFP. 15 June 2009.
  17. ^ "Announcement of opportunity for second flight of Vega small launcher in mid-2010". ESA. 25 July 2008.
  18. ^ "Italian Space Agency Plans its Relaunch". flightglobal.com. 31 October 2008.
  19. ^ Tariq Malik (12 March 2007). "Italian Firm Hails Test of Unmanned Spacecraft Prototype".
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