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Vega (launcher) |
 Vega rocket |
|
| Function | Small orbital launch vehicle |
|---|---|
| Manufacturer | ESA/ASI |
| Country of origin | Europe |
| Size | |
| Height | 30 m |
| Diameter | 3 m |
| Mass | 137,000 kg |
| Stages | 4 |
| Capacity | |
| Payload to LEO | 1,500 kg |
| Launch history | |
| Status | In Development |
| Launch sites | ZLV (ELA-1), Centre Spatial Guyanais |
| Maiden flight | Planned for 2009 |
| First stage | |
| Engines | 1 P80 |
| Thrust | 3040 kN |
| Burn time | 107 seconds |
| Fuel | Solid |
| Second stage | |
| Engines | 1 Zefiro 23 |
| Thrust | 1200 kN |
| Burn time | 71.6 seconds |
| Fuel | Solid |
| Third stage | |
| Engines | 1 Zefiro 9 |
| Thrust | 213 kN |
| Burn time | 117 seconds |
| Fuel | Solid |
| Fourth stage | |
| Engines | 1 AVUM |
| Thrust | 2.45 kN |
| Burn time | 315.2 seconds |
| Fuel | UDMH/N2O4 |
Vega (Vettore Europeo di Generazione Avanzata1, 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 named after 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. 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 Zefiro23 second stage, the Zefiro9 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 being France (12.43%), Belgium (5.63%), Spain (5%), The Netherlands (3.5%), Switzerland (1.34%) and Sweden (0.8%).
Contents |
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.
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.2
After a critical design review based on the completed first test firings3, 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.4
The Zefiro 23 second stage engine was first fired on 26 June 2006 at Salto di Quirra. This test was successful, too.5
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.6
The first test firing of the P80 first stage engine took place on 30 November 2006 in Kourou, and the test was concluded successfully.7
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.8
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.
| 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 |
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