Zefiro (rocket stage)

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.[5] After a critical design review based on the completed first test firings,[6] the second test-firing of the Zefiro 9 took place at Salto di Quirra on 28 March 2007. After 35 seconds, there was a sudden drop in the motor's internal pressure, leading to an increased combustion time.[7] On 23 October 2008, an enhanced version of the Zefiro 9 with a modified nozzle design and increased propellant load, the Zefiro 9A, was successfully tested.[8] On 28 April 2009, the final qualification test firing of Zefiro 9A took place at the Salto di Quirra Interforce Test Range in Sardinia, Italy.[9]

The Zefiro 23 was test fired twice on 26 June 2006 and 27 March 2008 at Salto di Quirra. Both tests were successful and the motor qualified for use on Vega.[10][11]

Zefiro 40 first test occurred on 8 March 2018 also at Salto di Quirra with a successful 92 seconds burn.[12]

A failure of the Zefiro 23 occurred shortly after the planned ignition during the Falcon Eye 1 mission on July 11 2019 which resulted in the loss of the satellite and a mission failure. The Zefiro 23 was supposed to fire for 77 seconds. Telemetry data showed the Vega rocket achieved a top speed of approximately 2.17 km/s, 233 seconds into flight. The rocket then deviated below its planned ascent trajectory before falling into the Atlantic Ocean north of the Guiana Space Centre.[13]

The propellant of all Zefiro models is HTPB 1912 with a nominal composition of 19% of aluminum powder, 69% of ammonium perchlorate with 12% of hydroxyl terminated polybutadiene binder.[14]

Zefiro 23 and Zefiro 9A, where the number represent the intended propellant weight at design phase, are used respectively as second and third stage of Vega rockets. Both motors have a 1.9 m diameter carbon epoxy filament wound case, a low density EPDM insulation, a flexible rocket nozzle joint and an electromechanical thrust vector control system.

Zefiro 23 is 7.5 meters tall and weighs 26 tonnes, of which 24 tonnes consist of solid propellant. It has a nominal burn time of 77 seconds with combustion chamber pressure of 95 bars.[2][15]

Zefiro 9A, designed and built exclusively with Avio technologies, is 3.5 metres tall, weighs 11.5 tonnes and burns 9 tonnes of solid propellant. It has a nominal burn time of 77 seconds with combustion chamber pressure of 95 bars. consumed in slightly more than 110 seconds.[1][15]

Zefiro 40, still in development phase as of 2019, is intended to be used as second stage of both Vega-C and Vega-E. In comparison to its predecessor Zefiro 23 the motor has an increased exercise pression, better structural load margins for both the casing and the propellant grains and an improved flexible rocket nozzle joint.[3]

• P80 (rocket stage)
• Solid rocket
• Vega (rocket)