Vega Launcher
Vega, an acronym for Vettore Europeo di Generazione Avanzata (European Advanced Generation Carrier), is an operational launcher in use by Arianespace, developed in collaboration between the Italian Space Agency (ASI) and the European Space Agency (ESA) for the launch into orbit of small satellites (300 -1500 kg).
The initial concept of the launcher project, known at first simply as ‘Zefiro’ from the name of the single propeller model envisaged in the original configuration, had been presented by the then BPD Defence Space to the ASI, in 1988, as the successor to the Scout launcher (used by the ‘Progetto San Marco’ programme) whose production was expected to be discontinued soon. The final Vega project was launched in 1998 with final approval by the European Space Agency. Italy is the largest funder and developer of the programme with a 65% share, followed by France (12.43%), Belgium (5.63%), Spain (5%), the Netherlands (3.5%) and finally with marginal shares Switzerland (1.34%) and Sweden (0.8%).
The Vega, named after the star of the same name in the constellation Lyra, is a single-body launcher, without side boosters, with three solid-propellant stages P80, Zefiro 23, Zefiro 9 and a liquid-propellant orbital manoeuvre stage, the AVUM.
The 4 stages of the Launcher
P80
Vega’s first stage in order of ignition, known as the P80, is the world’s largest and most powerful single-stage solid-propellant thruster. This programme was led by the Centre national d’Études Spatiales (CNES) in Évry and was financed by France (66%), Belgium, the Netherlands and Italy. Besides building the first Vega stage, the P80 project also aimed to develop new technologies useful for future developments of the Ariane series. The design of the stage was entrusted to the Italian Avio (engine) and the Italian-French Europropulsion (integration), as well as minor orders to the Belgian SABCA (control system), the French Snecma (exhaust nozzle) and the Dutch Stork B.V. (ignition system).
The stage is 11.20 metres high, has a diameter of 3 metres and a weight of 96.263 tonnes, of which 87.710 tonnes is propellant. The thrust produced by the engine, equivalent to 3 015 kN, is delivered for 109.9 seconds.
The P80 underwent two ignition tests, the first of which took place in Kourou on 30 November 2006 and was successfully completed: the engine performed very close to expectations.
The development of the project was then concluded with a second ignition test in Kourou on 4 December 2007, during which a new steerable nozzle was used. The engine generated thrust in line with expectations, allowing the stage to be declared ready for flight.
Zefiro 23 and Zefiro 9
ZEFIRO = ZEro FIrst stage ROcket motor derives from the original configuration of VEGA, which envisaged two equal Zefiros for the first two stages of the Launcher called zero stage and first stage.
The Zefiro 23 and Zefiro 9, where the number represents the weight in tonnes predicted at the start of the design, are the second and third stages of Vega respectively. They were developed, built and tested by Avio, with the collaboration of SABCA for the control system.
The Zefiro 23 underwent two firing tests at the Salto di Quirra firing range, the first on 26 June 2006, and the second on 27 March 2008. Both were successful and Zefiro 23 was declared airworthy.
Zefiro 9 also underwent two ignition tests at Salto di Quirra. The first, held on 20 December 2005, was a complete success; on the contrary, during the second, on 27 March 2008, which followed an overhaul based on data from the first test, the engine showed an abnormal drop in internal pressure.
The failure caused a delay in the development of the launcher, however, on 23 October 2008, during a new test, the engine showed satisfactory performance, also thanks to a new nozzle and a larger quantity of propellant.
AVUM
ZEFIRO = ZEro FIrst stage ROcket motor derives from the original configuration of VEGA, which envisaged two equal Zefiros for the first two stages of the Launcher called zero stage and first stage.
The Zefiro 23 and Zefiro 9, where the number represents the weight in tonnes predicted at the start of the design, are the second and third stages of Vega respectively. They were developed, built and tested by Avio, with the collaboration of SABCA for the control system.
The Zefiro 23 underwent two firing tests at the Salto di Quirra firing range, the first on 26 June 2006, and the second on 27 March 2008. Both were successful and Zefiro 23 was declared airworthy.
Zefiro 9 also underwent two ignition tests at Salto di Quirra. The first, held on 20 December 2005, was a complete success; on the contrary, during the second, on 27 March 2008, which followed an overhaul based on data from the first test, the engine showed an abnormal drop in internal pressure.
The failure caused a delay in the development of the launcher, however, on 23 October 2008, during a new test, the engine showed satisfactory performance, also thanks to a new nozzle and a larger quantity of propellant.
P80
Componente 1
Componente 2
Staffa
Diffuser
Diffuser 2
Diffuser 3
Diffuser 4
Raccordo
Raccordo 2
Raccordo 3
Raccordo 4
Raccordo 5
Raccordo 6
Zefiro-23
Staffe
Zefiro-9
Staffa
Staffa 2
Staffa 3
AVUM
Manifold
Staffette
Manifold
Manifold 2
Manifold 4
Manifold 5
Manifold 6
Manifold 7
P80
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