Since the late 1970's European Space Agency (ESA) and the commercial launch company Arianespace have operated the Ariane series of launchers. The current model, the Ariane 5 is one of the most succesful heavy lift launchers currently in operation. In recent years Arianespace has entered a joint venture with Russia's Starsem, the commercial operators of the venerable Soyuz launcher. This is a highly successful medium lift launch vehicle, with more than 1,700 launches to it's name. Currently a launch pad is being built at the European Kourou launch site in French Guiana for the Soyuz. This left a gap in the Ariane / Starsem capabilities - a light launch vehicle. ESA is developing a booster to fill this gap; the Vega launch vehicle.






Main Data
Height 30 m
Diameter 3 m
Liftoff mass 137 tonnes
Payload mass* 1500 kg



Although there is a growing tendency for satellites to become larger, there is still a need for a small launcher to place 300 to 2000 kg satellites, economically, into the polar and low-Earth orbits used for many scientific and Earth observation missions.
Europe’s answer to these needs is Vega, named after the second brightest star in the northern hemisphere. Vega will make access to space easier, quicker and cheaper.

Costs are being kept to a minimum by using advanced low-cost technologies and by introducing an optimised synergy with existing production facilities used for Ariane launchers.

Vega has been designed as a single body launcher with three solid propulsion stages and an additional liquid propulsion upper module used for attitude and orbit control, and satellite release. Unlike most small launchers, Vega will be able to place multiple payloads into orbit.

Development of the Vega launcher started in 1998. The first launch is planned for 2007 from Europe's Spaceport in French Guiana where the Ariane 1 launch facilities are being adapted for its use.

* Launch in circular orbit, 90°inclination, 700 km

Source: ESA - Launch Vehicles

Artist’s impression of the Vega launch vehicle climbing through the Earth’s atmosphere.

Credits: ESA - J. Huart

15 June 2006
Development of Vega, Europe’s new launcher for small payloads, continues at full speed. A dedicated test facility for the directional control system of the main engine has been completed and performance measurements are under way.

The Vega development programme is performing a crucial series of tests during 2006, including engine firings, mechanical and electrical performance verifications, and system-level trials. Among the many test campaigns, measuring the performance of the control loop of Vega’s first stage was started in May.
Vega's first stage, known as P80, is a solid-fuel rocket motor which includes a Thrust Vector Control (TVC) system consisting of two electromechanical actuators that operate a movable nozzle. The TVC system moves the nozzle to control the pitch and yaw of the launcher (the attitude of the vehicle in relation to the flight direction) during flight.


The Vega P80 thrust vector control system validation model, a structural model
representative of the interstage 0/1 stiffness and the actuator attachment points, with
a pressure vessel for the nozzle flexible joint. The thrust cone is visible, inverted within
the test apparatus. The exit of the nozzle is closed so that it and the flexible joint on
which it moves can be pressurised to simulate flight conditions. The pressurisation
system is below the metallic floor.

Credits: ESA - S Corvaja, ELV SpA, Avio SpA

In order to characterise the TVC behaviour under the various conditions that could occur during flight and to verify the functionality of the control loop, a dedicated validation facility has been constructed at ELV SpA, in Colleferro (Italy).

The TVC Validation Model allows examination of all aspects of system performance using fully representative hardware, specifically:

• the two electromechanical actuators, designed and manufactured by SABCA of Belgium
• their associated electronics unit – known as the Integrated Power Distribution Unit – also designed and manufactured by SABCA of Belgium
• a mechanically representative model of the rocket nozzle – designed and manufactured by Snecma Propulsion Solide of France
• a battery set employing lithium-ion technology – to provide a more complete representation of operational conditions in some test scenarios – designed and manufactured by Saft of France.

The control room for the Vega P80 Thrust Vector Control system validation model,
from which the tests are controlled and the measurements recorded. The control room
is situated in a strengthened bunker to protect the occupants from any risk linked to the
pressurisation system

Credits: ESA - S Corvaja, ELV SpA, Avio SpA

The design, manufacture and assembly of the components of the TVC Validation Model have been lead by Europropulsion SA, a jointly-owned subsidiary of Snecma Propulsion Solide (France) and Avio SpA (Italy), which is the Prime Contractor for the P80 main engine. The construction of the test plant, including mechanical parts and ground support equipment for electronic command and measurement acquisition, has been carried out under the responsibility of ELV SpA, the Prime Contractor for the Vega launch vehicle. The management of the P80 demonstrator programme is under the responsibility of the P80 Integrated Project Team (ASI , CNES and ESA), located at the CNES facility in Evry, France.
The TVC subsystem tests are expected to last for several months. They will allow checking of the control sequence that will be used during the first P80 motor static firing test, scheduled to be conducted in Kourou during the last quarter of 2006.

At a later stage, during the system test campaigns, the TVC Validation Model will also be used for overall system verification. It will be controlled by a test version of the Vega onboard computer and flight software, making use of the inertial measurement system simulator and the simulated flight dynamics environment.

Source: ESA - News

A static test firing of the Zefiro 23 second-stage engine of
Europe's new Vega launch vehicle was conducted on Monday
26 June 2006, at the Italian Ministry of Defence test centre in
Salto di Quirra, Sardinia.

Credits: ESA-S. CORVAJA

26 June 2006
ESA PR 21-2006. ESA’s Vega small satellite launch vehicle has made a new step toward its maiden flight, late next year, with the success of the first firing test on its second stage motor, the Zefiro 23.

The static firing was performed today, 26 June, at the Italian Ministry of Defence test centre in Salto di Quirra, Sardinia. The 7.5m tall, 2m diameter motor, featuring a carbon epoxy filament wound casing, delivered more than 100 metric tons of thrust (1,070 kN), burning some 24 metric tons of solid propellant in 75 seconds.
Numerous data were gathered during the test and are now under analysis to improve technical knowledge of the motor’s behaviour and refine the launcher’s future performance. Also tested during the firing were various subsystems, including a thrust vector control system that will steer the motor’s nozzle to provide flight control. After this success, the motor will proceed with its critical design review, at which stage its technical characteristics will be finalised.


A static test firing of the Zefiro 23 second-stage engine of Europe's new Vega launch
vehicle was conducted on Monday 26 June 2006, at the Italian Ministry of Defence test
centre in Salto di Quirra, Sardinia.

Credits: ESA-S. CORVAJA

Built by Avio in Colleferro, near Rome, the Zefiro 23 motor will be the basis for the second stage of ESA’s Vega launcher. The first firing test with the third stage motor – the Zefiro 9 – was performed in December 2005. Conducted on behalf of ESA’s Vega development programme, these two firing tests followed three static firings of the Zefiro 16 demonstrator in 1998, 1999 and 2000. Both the Zefiro 23 and Zefiro 9 will undergo an additional ground firing test each to complete their development and qualification.

“The Zefiro 23 is one of the largest composite casing solid rocket motors ever test fired in Western Europe, noted Antonio Fabrizi, ESA’s director of launchers, but it will be dwarfed shortly, when we will fire Vega’s first stage motor, the P80, with its 88 tons of propellant, in Kourou, French Guiana, in November.”

“With this new motor firing, the Vega programme has passed another milestone in good time”, continued Fabrizi, “and I praise our industrial team as well as our partner the Italian Space Agency, for this achievement. Now let’s proceed and make sure we will be able to meet our schedule for the next phases.”

The first Vega flight is currently set for the end of 2007 from Europe’s Spaceport in French Guiana.


Artist’s impression of the Vega launch vehicle climbing through the Earth’s atmosphere.

Credits: ESA - J. Huart

Under development since 1998 with the support of seven ESA Member States (Italy, France, Belgium, Switzerland, Spain, the Netherlands and Sweden), ESA’s Vega small satellite launcher is an all-solid three-stage vehicle with a liquid-fuelled injection module. ELV SpA, a joint venture of Avio and ASI, the Italian Space Agency, was delegated the responsibility for Vega development. CNES, the French space agency, holds similar responsibility for the P80 first stage.

Vega is designed to loft single or multiple payloads to orbits up to 1,500 km in altitude. Its baseline payload capability is about 1,500 kg to a circular 700-km high sun-synchronous orbit but it can also loft satellites from 300 kg to more than 2 metric tonnes, as well as piggyback microsatellites. This range of performance covers the needs for multiple applications in the fields of remote sensing, environmental monitoring, Earth science, space science, fundamental science and research and technology for future space applications and systems. Once qualified, Vega will be marketed and operated by Arianespace, as a complement to Ariane 5 and Soyuz, and will address the small satellite launch market.

Source: ESA - News

Integrated nozzle for P80 motor, before shipment to French Guiana.

15 September 2006
On 14 September 2006 a ceremony took place at the facilities of Snecma Propulsion Solide (SPS) in Bordeaux, France, to mark the occasion of the delivery of the first nozzle for the P80 solid rocket motor. The P80 is the first stage of the Vega small launcher.

The P80 nozzle delivery is a key milestone for the Vega programme. It is the result of several years of intensive development activities, during which Snecma Propulsion Solide performed the detailed definition of the various components of the nozzle, and validated new manufacturing processes. They achieved a major step forward in this area of technology aimed at reducing costs. This is a major event for Vega but it is also a precursor to future updates in the design of Ariane 5 boosters.


Integrated Elements of the qualification model of the P80 nozzle before their integration.
From left: J. Pasquier, CEO Europropulsion, and P. Pascal, CNES P80 project manager.

Once arrived in Kourou, the completed nozzle will be integrated with the P80 solid rocket motor, under preparation, for the first firing test planned for end November 2006.
The delivery was also an opportunity to acknowledge the significant work performed by the industrial teams at SPS and to recognise its industrial capability in space activities. SPS undertakes diverse activities in the area of military systems and in space programmes, with its involvement in Ariane 5 and Vega. Together, these activities permit SPS to take a long term view regarding the industrial teams and allow the maintenance of industrial capability in solid propulsion, both in development and production.


Speech of Antonio Fabrizi, ESA Director of Launchers during the ceremony for the delivery of the P80 Nozzle.
Also present at the ceremony: M. Eymard, CNES Director of Launchers; S. Scippa, CEO ELV SpA; J. Pasquier, CEO Europropulsion; G. Lasagni, Avio Space Business Unit; M. Laroche, SPS; P.Bonguet, Programmes Director Arianespace.

The ceremony was attended by ESA’s Director of Launcher Programmes, Mr Antonio Fabrizi, as well as representatives from the French National Space Agency (CNES), Arianespace (France), Europropulsion (France), AVIO SpA (Italy), Snecma Propulsion Solide (France) and ELV SpA (Italy). A short roundtable allowed an exchange of views on the launcher sector and its ongoing evolution.

Source: ESA - News

Structural model of the upper composite of the Vega launch
vehicle on the 'multishaker' electrodynamic shaker in the
Test Centre at ESA-ESTEC. The octagonal structure at the
top of the image is a mechanically representative model
of a payload.

Credits: ESA - A.Le Floc'h

5 October 2006
The upper composite of ESA’s new small launcher has passed its vibration tests at ESA's European Space Research and Technology Centre (ESTEC) with flying colours. Vega’s components are built and tested at various locations across Europe. The first launch is planned for the end of 2007 from Europe’s Spaceport in Kourou, French Guiana.

Vega, which is being built by European industry under the leadership of ELV SpA (Italy), is a small launch vehicle designed to carry payloads in the range 300 kg to 2.5 tonnes into low Earth orbits. The typical reference for Vega’s launch capacity is to carry 1500 kg to a 700 km-altitude polar orbit. Vega will be particularly suitable for the launch of scientific and Earth observation missions.

Vibrations


Artist’s impression of the Vega launch vehicle climbing through the Earth’s atmosphere.

Credits: ESA - J. Huart

During the launch of a rocket, vibrations occur due to engine ignition, the thrust of the engines and the high-speed flow of air over the body of the vehicle as it accelerates through the Earth’s atmosphere.
The upper composite that has just been tested is the top part of the launcher, which houses the navigation, communications and control equipment. The payload is carried on top of the composite, protected by a streamlined fairing, or nosecone. During testing, a mechanically representative model of a real satellite was used.

In order to confirm that the upper composite will be able to withstand the vibrations that it will experience during launch, it was mounted on the ‘multi-shaker’ in the Test Centre at ESTEC. This electrodynamic vibration table applied accelerations to the base of the composite while around 400 accelerometers and 40 strain gauges measured the movements and forces within the structure. This confirms that the design calculations are correct.

“The vibration tests went well and we are on schedule” said Vega Test Manager Wolfgang Teichert. “We have carried out most of the tests for the final stage of the launcher”.

Final exam


Structural model of the upper composite of the Vega launch vehicle on the 'multishaker'
electrodynamic shaker in the Test Centre at ESA-ESTEC. The octagonal structure at
the top of the image is a mechanically representative model of a payload.

Credits: ESA - A.Le Floc'h

At the end of 2006, reports on all the tests will be presented at the ‘Critical Design Review’. If Vega passes this ‘final exam’, production of components for the qualification flight launcher can proceed.


Industry day

The fourth Vega industry day is taking place on Thursday 5 October 2006 at ESA-ESTEC and the adjacent Space Expo in Noordwijk, The Netherlands. All the space industry members committed to the Vega Small Launcher programme are involved. The industry day is an occasion for all participants in the Vega programme to share an overview of the key technical and programmatic achievements in the development activities being carried out under the responsibility of the three main industrial contractors for the Vega programme:

• Vitrociset SpA (Italy) – ground segment
• Europropulsion SA (France/Italy) – solid propellant motor and P80 first stage
• ELV SpA (Italy) – launch vehicle

It will also be an opportunity to focus on the upcoming programme milestones leading to the qualification flight. Later flights, planned in the context of the Vega Research and Technology Accompaniment (VERTA) programme, will also be discussed. VERTA includes support for five demonstration flights that will serve to launch selected ESA payloads and showcase Vega’s capabilities.

Source: ESA - News

The Centre National d’Etudes Spatiales (CNES)+ press release is reproduced below:

24 November 2006

Europe’s family of launchers is set to grow, with a kid brother for Ariane 5 called Vega expected some time late next year. Vega is designed for the launch of small satellites, complementing its larger stable mate. The Vega project was initiated by ESA in 1999. CNES is leading development of the P80 engine that will power the 1st stage of the new launcher.

The P80 will in fact carry 88 tonnes of solid fuel needed to get the light Vega launcher off the ground.


Vega Launcher (artist's view).
Copyright : ESA/Jacky Huart


This new engine will mark a major step forward in solid propulsion technology.


Innovating …


The P80 is the 1st of a new generation of solid rocket boosters. Each of the engine’s materials and components is the result of research into space technologies. The architectures of the igniter and nozzle have been simplified, and performance-enhancing materials have been used for the engine casing and thermal protection.

A reduction in costs


All the innovations on the P80 are intended to bring down recurring costs. For the project contractors, P80 is an opportunity to experiment and invest for the future, since the new engine will not only power Vega but also serve as a testbed for technologies that may be employed in the near future on the larger boosters of heavy-lift launchers like Ariane 5.


P80 : Transfer from BIB* to BETS** (Kourou, 07-11-06)
Copyright : ESA-CNES 2006, CSG/Ph. Baudon

Certain project partners are therefore contributing funding to the project and have helped to trim development costs, which is a vital factor in this highly competitive arena.

After the manufacturing and validation phases, the first test rig firing is scheduled for 30 November 2006 in French Guiana, overseen by the Ground Systems Sub-Directorate (SDS) of CNES’s Launchers Directorate (DLA), assisted by Europropulsion.

Teams are pulling out all the stops to make this firing test a success, coming after the successful 1st tests of the Zefiro 9 and Zefiro 23 engines that will power Vega’s 3rd and 2nd stages, respectively.


* BIB : Booster Integration Building
** BETS : Booster Engine Test Stand

+CNES is the French National Space Centre

Source: CNES Press Release

Artist’s impression of the Vega launch vehicle climbing through the Earth’s atmosphere.

Credits: ESA - J. Huart

27 November 2006
On 30 November, the P80 motor which is to power Vega’s first stage will undergo its maiden static firing on the same test pad used to demonstrate Ariane 5’s solid booster stages in Kourou, French Guiana.

The Solid Booster Test Bench (BEAP) is the unique test pad at the Guiana Space Centre, Europe’s Spaceport. Since 1993, it has seen the successful testing of Ariane 5 Solid Booster Stage (EAP) motors. Of course, none was actually intended to lift off and the facility is equipped with safety systems to prevent a booster breaking loose from the test bench and leaving the ground. In this case, large blades would cut its envelope open, allowing the solid propellant to burn freely without providing any thrust.

Recently, the BEAP has been modified in order to accommodate a different kind of booster for static firing. While it shares its three metre diameter with Ariane 5's booster stages, the P80 motor is much shorter than the 31.2-metre-tall EAP – it is only 11.7 metres high. Nevertheless, it is the largest European solid rocket motor of its kind.

The largest monosegment booster


Artist's impression of Vega on the launch pad at Europe's Spaceport in French Guyana.

Credits: ESA-J.Huart

Unlike the EAP’s motor, whose 238-tonne propellant load is cast in three segments which are later assembled together, the P80 features only a single segment with about 88 tonnes of solid propellant. Although this is less than the biggest of the EAP segments, it is far more than any other composite single-segment solid motor ever tested. For comparison, to date the record is held by the motor of the SRB-A booster stage on Japan’s H-2A launcher, with 66 tonnes of solid propellant.

The P80’s propellant load was cast some 6 km from the BEAP, at the Guiana Propellant Plant (UPG) where the EAP’s lower segments are also loaded. In fact, the P80 used the same pit. After an initial test with inert propellant in April 2004, real propellant was poured in the first qualification model of the P80 last August.

“The propellant is not exactly the same as on the EAP’s”, explains Stefano Bianchi, Vega Programme Manager at ESA. “We adapted the propellant mix and the granulometry to increase its performance and density.”

As for the EAP segments, once the propellant’s polymer binder had solidified, the mandrel forming the exhaust canal for hot gases was extracted and the motor underwent numerous inspections to make sure that no bubbles or cracks had formed inside the binder. In a solid motor, these kinds of defects could have explosive consequences. After inspection, the motor was prepared for its test firing.

The P80 is not simply the new motor developed for the first stage of ESA’s Vega small launch vehicle. It is a multidisciplinary demonstrator to validate advanced technologies which could later be applied to Ariane 5’s boosters.


Technological advances

The most obvious change is to the booster casing. It is made of filament wound graphite epoxy, a technology largely used on smaller motors for civilian launchers as well as ballistic missiles. Much lighter than the stainless steel currently used on Ariane boosters, it provides a dramatic increase in payload capacity.

Other improvements in the motor include a new design of igniter with a simplified architecture, also using a carbon-fibre case.

The P80 nozzle looks like a shorter version of the EAP nozzle but its design was revised to achieve more simplicity, incorporate fewer elements, and reduce production costs. New thermal insulation material and a narrower throat improve the expansion ratio and overall performance. The new type of flexible joint makes it a lot easier to steer and has allowed the replacement of heavy hydraulic actuators by much lighter electromechanical ones for thrust vector control.

“There are lots of challenges on this test”, says Stefano Bianchi. “As on every maiden firing, there is also a lot to learn.”

Preparing for Vega


Artist's impression of Vega on the launch pad at Europe's Spaceport in French Guyana.

Credits: ESA-J.Huart

The firing test is planned for 30 November at around 15:00 UTC/GMT (12:00 local time, 16:00 CST/Paris). The timing will depend on wind conditions, to make sure the cloud resulting from the exhaust will not drift over populated areas.

The test will last about 100 seconds, with the motor delivering some 200 tonnes of average thrust.

Developed under a separate programme managed by an integrated team led by CNES, the French space agency, on behalf of ESA, the P80 is the last of Vega’s motors to undergo static firing. The Zefiro 9 and the Zefiro 23, due to power the third and second stages of ESA’s small launch vehicle, were test fired in December 2005 and June 2006 respectively, at Italy’s test centre in Salto di Quirra, Sardinia.

After the 30 November test, it is planned that each of the three motors will undergo an additional static test before the maiden flight of the Vega launcher, which will complement Ariane 5 and Soyuz in the small satellite segment of the launch market.

Source: ESA - News

Vega’s first-stage motor came to life on 30 November 2006 at 12:30 Kourou time
(15:30 UT) when it was ignited for its first static firing test at the Guiana Space Centre,
Europe’s Spaceport, in Kourou, French Guiana.

Credits: ESA/CNES-SOV

30 November 2006
ESA PR 42-2006. The largest European mono-segment filament-wound case solid propellant motor ever developed came to life at 12:30 Kourou time today (15:30 UT) when it was ignited for its first static firing test at the Guiana Space Centre,
Europe’s Spaceport, in Kourou, French Guiana.

Watch the firing of Vega's first-stage motor

The P80 motor - which will power the first stage of ESA’s Vega launch vehicle - delivered a mean thrust of about 190 tonnes for over 100 seconds, representing roughly one third of the thrust delivered by each of Ariane 5’s solid booster stages (EAPs). A peak of 250 tonnes was reached 7 seconds into the test.

“The first data we have at hand show that the firing closely followed the predicted pressure curve” said Antonio, Fabrizi, ESA’s Director of Launchers. “ This event concludes the first set of development tests conducted for the Vega launcher in 2006, a very intensive and successful year for the Programme. This excellent result marks a milestone that contributes significantly to further increasing confidence in the Vega launcher, the exploitation of which is currently being prepared by Arianespace following the signature of a Convention with ESA in November this year.”

“Among the various features of the P80 programme, beyond the technical achievements and the innovation involved, it is important to underline the remarkable contribution in terms of industrial investment, made possible by the expectations of a successful exploitation of the Vega launcher,” added Fabrizi.

More than 600 parameters were recorded in the course of the firing test to check that the many new technologies introduced in this motor performed as intended.

Based on the industrial capability acquired with the three-segment Solid Rocket Motor powering Ariane 5’s EAP and about the size of one of their lower segments, the P80 motor features many new developments which might later be used on Europe’s workhorse heavy launcher to improve its performance in terms of capabilities and cost.

A technology demonstrator


Vega P80 first stage motor being transferred from the Booster
Integration Building (Bâtiment d'Intégration des Propulseurs -
BIP) to the Booster Engine Test Stand (Bâtiment d'Essai
d'Accélérateur à Poudre - BEAP)

Credits: ESA/CNES-SOV

About 12 m high and 3 m in diameter, the P80 motor is loaded with 88 tons of solid propellant. Unlike previous motors of this size or larger developed in Europe or in the rest of the world, it is made of a single propellant segment instead of several segments cast separately before being assembled together.

Taking advantage of its common dimensions, the propellant casting was carried out at the Guiana Propellant Plant (UPG) in Kourou, in the same pit as the 100-tonne lower segments of Ariane 5’s EAPs. However, instead of the EAP’s stainless steel outer structure, P80 has a lightweight filament-wound composite casing. It also incorporates a newly simplified design of igniter with a carbon fibre structure.

A new composite steerable nozzle was developed, with a simplified architecture made of fewer elements to reduce production costs. It also includes complex-formed cast metal parts and a new thermal insulation material. The nozzle joint was made more flexible than on previous models to facilitate thrust vector control through electromechanical actuators. This is an additional technology improvement on a motor of that size, as they usually rely on a more complex hydraulic system.

“As expected, the P80 withstood high combustion pressure, of above 80 bars,” commented Stefano Bianchi, Vega Programme manager at ESA. “Despite this highly demanding environment, it apparently performed perfectly, although we’ll need some more time to fully analyse the vast amount of data we have just collected.”

Today’s test was performed on the solid booster test stand (BEAP) in Kourou, the same facility used for firing tests on Ariane 5’s EAPs. The motor will now be disassembled for detailed analysis. Some of its parts, such as the nozzle, will be returned to Europe.

New step towards Vega


Artist's impression of Vega on the launch pad at Europe's Spaceport in French Guyana.

Credits: ESA-J.Huart

The P80 is developed both as Vega’s first stage and as a technology demonstrator under a specific ESA programme managed by an integrated project team led by CNES, the French space agency, with an industrial team led by the French-Italian joint-venture Europropulsion, under delegation from Avio SpA of Italy. Among the main industrial subcontractors involved in the P80 are SABCA of Belgium (thrust vector control system), Snecma Propulsion Solide of France (nozzle) and APP of the Netherlands (igniter).

This was the first of two firings for the P80. A second test is tentatively planned by mid 2007. Additional test firings of the Zefiro 23 and then the Zefiro 9 motors – which will power Vega’s second and third stages - are also scheduled in 2007. This P80 firing test is a major achievement for the Vega Programme, as well as for solid propulsion capability in Europe and completes the series of major Vega milestones planned and completed in 2006. This demonstrates the programme maturity and allows to perform the final consolidation of the planning for the remaining activities, clearing the way to the Vega maiden flight in 2008.

ESA’s Vega small satellite launcher is an all-solid three-stage vehicle with a liquid-fuelled injection module, developed with the support of seven ESA Member States (Italy, France, Belgium, Switzerland, Spain, the Netherlands and Sweden). ELV SpA, a joint venture of Avio SpA and ASI, the Italian Space Agency, was delegated the responsibility for Vega launcher development.

Vega is designed to lift single or multiple payloads to orbits of up to 1,500 km in altitude. Its baseline payload capability is about 1,500 kg to a circular 700-km-high sun-synchronous orbit but it can also loft satellites ranging from 300 kg to more than 2 tonnes, as well as piggybacking microsatellites. This range of performance covers the needs for multiple applications in the fields of remote sensing, environmental monitoring, Earth science, space science, fundamental science and research and technology for future space applications and systems. Once qualified, Vega will be marketed and operated by Arianespace at the Guiana Space Centre , as a complement to Ariane 5 and Soyuz, and will address the small to mid-sized satellite launch market.

Source: ESA - News

29 March 2007


Artist's view of Vega on the launch pad at Europe's Spaceport in French Guiana

Credits: ESA - J. Huart

On Wednesday 28 March, at around 15:00, the second firing test of the solid rocket motor ‘Zefiro 9’ – the motor that will power the third stage of ESA’s future small launcher Vega - took place at the Salto Di Quirra Inter-force Test Range in Sardinia, Italy.

The first results of the test indicate that the behaviour of the motor and the actuation of the nozzle were in accordance with predictions up until 35 seconds after ignition, when a sudden drop in the motor’s internal pressure was detected. The pressure stabilised at a value lower than the nominal, leading to a longer combustion time than the expected 105 seconds.

More than 400 sensors fitted to the motor monitored its behaviour during and after the firing test. The first visual investigation conducted on site after the firing showed that the nozzle of the motor was damaged, but no further damage was observed on the motor case or on the test bench.

ESA and Industry teams have already started a thorough analysis and assessment of the data collected during the test. The causes of the anomaly have not been identified yet and an investigation board is being set up for this purpose. The board shall recommend preventative and other appropriate actions to preclude the recurrence of similar anomalies for the finalisation of the motor qualification.


Successful firing test of Vega's Zefiro 9 engine in December 2005 in Sardinia

Credits: Avio

This was the second firing test of the Zefiro 9 motor. The first test took place successfully in December 2005. The first firing tests of the other Vega solid rocket motors - Zefiro 23 (second stage) and P80 (first stage) held on 26 June 2006 at Salto di Quirra and on 30 November 2006 in Kourou respectively, also went well. Three more firing tests, in the years 1999-2000, were conducted successfully for the Zefiro 16 motor, the forerunner of the Zefiro family of solid rocket motors.

The Zefiro 9 motor is developed by AVIO SpA and is based on advanced technologies in the field of solid rocket propulsion. It has an overall height of 3.17 m and a diameter of 1.92 m, contains approximately 10 tonnes of propellant and provides a maximum thrust of 305 kilonewton in vacuum.

Vega is a single body launcher composed of three solid propellant stages and a liquid propellant upper module. It is approximately 30 metres high and weighs a total of 137 tonnes at lift-off. Vega will be able to launch satellites of up to 1500 kg into a 700 km-altitude polar orbit, and it will also be useable in a wide range of scientific and Earth observation missions. The maiden flight for ESA’s small launcher remains scheduled to take place in 2008.

The Vega launcher is being developed with the support of seven ESA Member States (Italy, France, Belgium, Switzerland, Spain, the Netherlands and Sweden). ESA has contracted the development activities of the launcher to ELV SpA, a joint venture between Avio SpA and the Italian Space Agency (ASI).

Source: ESA - News

16 October 2007



The development of the on-board computer for the Vega launcher has reached an important milestone with the successful completion of flight qualification activities. The computer is one of the first units in the Vega programme to achieve qualification.

Saab Space has been in charge of the development of this new generation of On-Board Computer (OBC), with an architecture based on the ERC-32 CPU kernel and a Saab Space developed Computer Core Support (COCOS) ASIC. Compared with today's Ariane 5, the VEGA OBC provides more than 10 times higher performance with 4 times more RAM. It is contained in a slim mechanical package that consumes just 25% of the volume and less than half of the total mass of its predecessor, while at the same time being more tolerant of the space radiation environment. Saab Space has also developed the embedded software for boot and ground services, together with the LN-1 low-level flight software.



Leif Johansson, Saab Space project manager for the Vega OBC, expressed his satisfaction with this major achievement: “We are now looking forward to confirmation of the good test results and excellent performance of the OBC through the verification that will be carried out at system level and, later on, with the qualification flight.” Mr Johansson also warmly congratulated his team for the good work they have performed.

Saab Space has a well-known and widely acknowledged expertise in this domain, having already developed the OBCs for the Ariane launcher family and for other space applications.

Several models of the Vega OBC have been produced, beginning with the structural and engineering models needed for the development and qualification activities and for the software and system validation that was carried out in Europe and French Guiana. Completion of qualification means that the first flight model will be delivered in the near future for integration into the avionics module of Vega's AVUM (Attitude and Vernier Upper Module) restartable fourth stage.

The Vega Launch Vehicle Programme is managed by the ESA Integrated Project Team from ESA-ESRIN. Once Vega becomes operational, following a maiden flight scheduled for the end of 2008, it will be able to place satellites with masses of 300 to 2000 kilograms economically into the polar and low-Earth orbits used for many scientific and Earth observation missions.

Source: ESA - Launchers

5 December 2007

P80 static firing test being performed on 4 December 2007, using the solid booster test stand (Bâtiment d'Essai d'Accélérateur à Poudre - BEAP) at the Guiana Space Centre, Europe's Spaceport in Kourou, French Guiana. This is the same facility that is used for firing tests on Ariane 5's solid-propellant boosters.

Credits: ESA / CNES / CSG-SOV

A prototype of the P80 rocket motor, which will power the first stage of ESA's new small launcher - Vega, was successfully tested on 4 December at the Guiana Space Centre, Europe's Spaceport in Kourou, French Guiana. Ignition occurred at 12:35 local time (15:35 UTC/GMT).

The motor delivered a mean thrust of about 190 tonnes for a nominal duration of 111 seconds. This is roughly one third of the thrust delivered by each of Ariane 5's solid booster stages.

More than 600 parameters were recorded during the firing test to monitor the performance of the motor. Initial analysis confirms that the measurements are fully in line with predictions.

Solid propellant rockets cannot be shut down once they have been ignited. The test engine was equipped with specially designed cutters to break open the casing and stop the test, should a malfunction have made this necessary.

Qualification for flight

P80 static firing test being performed on 4 December 2007, using the solid booster test stand (Bâtiment d'Essai d'Accélérateur à Poudre - BEAP) at the Guiana Space Centre, Europe's Spaceport in Kourou, French Guiana. This is the same facility that is used for firing tests on Ariane 5's solid-propellant boosters.

Credits: ESA / CNES / CSG-SOV

The first firing of the P80 took place on 30 November 2006. This was a qualification model and served to finalise the validation of the motor behaviour predictions and of the chosen technologies.

The motor tested yesterday was representative of the flight configuration. Once the data recorded during the test have been analysed and the engine has undergone post-test inspection, this firing is expected to complete qualification of the P80 in readiness for Vega's maiden flight, scheduled to take place by the end of 2008.

The P80 motor is about 12 metres high and 3 metres in diameter, and is loaded with 88 tonnes of solid propellant. Unlike previous motors of this size, it contains a single propellant segment, instead of several segments cast separately before being mated together.

Taking advantage of its similar dimensions, the propellant casting for the P80 is carried out at the Guiana Propellant Plant in Kourou, in the same pit as the 100-tonne lower segments of Ariane 5's solid boosters. However, instead of the steel outer structure used for the Ariane boosters, the P80 has a lightweight, filament-wound composite casing. It also incorporates a new, simplified design of igniter with a carbon fibre structure.

A new, steerable nozzle fabricated from composite material has been developed, with a simplified architecture made up of fewer elements, to reduce production costs. It also includes complex-formed cast metal parts and a new thermal insulation material. The nozzle joint is more flexible than on previous engines, allowing thrust vector control by means of electromechanical actuators. This is an additional technological improvement on a motor of this size, which usually needs to employ a more complex hydraulic system.

P80 static firing test being performed on 4 December 2007, using the solid booster test stand (Bâtiment d'Essai d'Accélérateur à Poudre - BEAP) at the Guiana Space Centre, Europe's Spaceport in Kourou, French Guiana. This is the same facility that is used for firing tests on Ariane 5's solid-propellant boosters.

Credits: ESA / CNES / CSG-SOV

“The first data received show that the pressure curve is following perfectly the prediction. It is an outstanding result,” said Caroline Cros, the ESA team member responsible for P80 development “and I congratulate the industrial team, as well as our CNES and ASI partners, for this achievement.”

Today's test was performed on the solid booster test stand (Bâtiment d'Essai d'Accélérateur à Poudre - BEAP) in Kourou, the same facility used for firing tests on Ariane 5's solid-propellant motors. The P80 will now be disassembled for detailed inspection. Some of its components will be returned to Europe for examination and analysis.

“The qualification of the P80 motor is a cornerstone. It is the biggest mono-segment, filament-wound-case solid-fuel rocket motor ever developed and this takes us a step closer to the Vega maiden flight,” said Stefano Bianchi, ESA's Head of the Vega programme. “The programme has a tight schedule for the maiden flight. We can proceed - as from today - with increased confidence. Let's make sure we will meet the next major milestones as scheduled.”

About P80 and Vega

The P80 is being developed both as Vega's first stage and as a technology demonstrator. The development is part of the Vega programme, managed by an integrated project team led by ESA and involving staff from ESA, ASI - the Italian Space Agency and CNES - the French space agency. CNES also has a major responsibility in the management of the P80 development.

The industrial team is led by the French-Italian joint venture Europropulsion, under delegation from Avio SpA of Italy. Among the main industrial subcontractors involved in the P80 are SABCA of Belgium (thrust vector control system), Snecma Propulsion Solide of France (nozzle) and APP of the Netherlands (igniter).

ESA's Vega small satellite launcher is an all-solid-propellant, three-stage vehicle with a liquid-fuelled injection module, developed with the support of seven ESA Member States (Italy, France, Belgium, Switzerland, Spain, The Netherlands, and Sweden).

ELV SpA, a joint venture between Avio SpA and ASI, is the prime contractor for the Vega launcher development.

Vega is designed to lift single or multiple payloads to orbits of up to 1 500 km in altitude. Its baseline payload capability is to carry 1 500 kg to a circular, 700 km altitude, Sun-synchronous orbit. It can launch satellites ranging in mass from 300 kg to more than 2 tonnes.

This range of performance covers the needs of multiple applications in the fields of remote sensing, environmental monitoring, Earth science, space science, fundamental physics and research and technology for future space applications and systems.

Once qualified, Vega will be marketed and operated by Arianespace at the Guiana Space Centre, as a complement to Ariane 5 and Soyuz. It will serve the small to mid-sized satellite launch market.

Source: ESA - News

20 December 2007


The modal characterisation test for Vega - ESA's new, small launcher - has been successfully completed at the premises of IAB GmbH in Ottobrunn, Germany.

The goal of the Modal Characterisation Test (MOCO) was to obtain the launch vehicle's modal parameters, in order to improve the robustness of the data (bending mode frequencies, shape and damping) used in the design of the guidance and control algorithms.

The MOCO test specimen consisted of a structural model of the launcher and payload, without its first stage and payload fairing. Its total height was 16.3 meters, with a mass of 40 tonnes. The model was rigidly mounted on the test site's 800 tonne seismic mass.



“We had to organise the test campaign, manage the logistics to obtain all the elements from several places in Europe and assemble, here in Munich, three-quarters of the Vega launcher for the first time. It was really challenging, but we managed to make it in two months,” said Raffaele di Stefano (ELV), the AIT manager for the MOCO test.

The test technical responsible, J. L. Leofanti (ELV) - reviewing the test execution and results - said: “when we reached the structural resonance, with the launcher moving several centimetres at the tip, our minds were completely concentrated on the test results, but at the same time we felt a great satisfaction with the job done.”



Vega is a single body launcher composed of three solid propellant stages and a liquid propellant upper module. It is approximately 30 metres high, with a total mass of 137 tonnes at lift-off. Vega will be able to launch satellites of up to 1500 kg into a 700 km-altitude polar orbit, and it will be usable for a wide range of scientific and Earth observation missions. The maiden flight is scheduled to take place towards the end of 2008.

The Vega launcher is being developed with the support of seven ESA Member States (Italy, France, Belgium, Switzerland, Spain, the Netherlands and Sweden). ESA has contracted the development activities of the launcher to ELV SpA, a joint venture between Avio SpA and the Italian Space Agency (ASI).

Source: ESA - Launchers

31 March 2008
Zefiro 23 second firing test, conducted at the Salto Di Quirra Inter-force Test Range in Sardinia, Italy, on 27 March 2008.

Ignition of the qualification model of the Zefiro 23 solid-propellant rocket motor occurred at 13:15 CET. In just 14 seconds, the thrust reached 930 kN, equivalent to nearly 95 tonnes of force.

This was the second and final firing test for the Zefiro 23, in which over 24 tonnes of propellant was consumed with a flame temperature of over 3000 K. The burn lasted approximately 75 seconds and initial results show the test to be a success.

Credits: AVIO Space

On 27 March 2008, the second stage motor for Vega - Europe's new small launcher - successfully completed a static firing test at the Salto Di Quirra Inter-force Test Range in Sardinia, Italy.

Ignition of the qualification model of the Zefiro 23 solid-propellant rocket motor occurred at 13:15 CET. In just 14 seconds, the thrust reached 930 kN, equivalent to nearly 95 tonnes of force.

This was the second and final firing test for the Zefiro 23, in which over 24 tonnes of propellant was consumed with a flame temperature of over 3000 K. The burn lasted approximately 75 seconds and initial results show the test to be a success.

Performance as predicted

The combustion chamber pressure and motor thrust were well within the test prediction. Large amplitude movements of the thrust vector control system were executed - simulating worst-case manoeuvres - and the performance was very satisfactory. Additionally, modifications implemented in the nozzle design following the anomaly experienced during the previous Zefiro 9 test were proven to be effective.

“The success of this test demonstrates the soundness of the design and rewards the enormous efforts of the team that has worked on the project,” stated Francesco Betti, Head of the Design Department at Avio's Space Division.

The motor will now be transported back to Avio's facility at Colleferro (Italy) for a thorough inspection of all its components and the data obtained from the 400 sensors deployed during the test will be analysed in more detail.

“The project team will rendezvous at Salto Di Quirra in June for the Zefiro 9 firing test,” announced Paolo Bellomi, Technical Director of ELV, the Vega launcher prime contractor.


Two motors now qualified

In the past 27 months, four Vega test firings have taken place at Salto Di Quirra, each one a milestone in the development of the Vega launcher. The Zefiro 23 is the second Vega solid rocket motor to achieve qualification, following the P80 first stage motor, which completed qualification testing in December 2007.

“The teams of Avio, ELV, SABCA APP and of the Integrated Programme Team of ESA, CNES and ASI did a great job. This success paves the way for the Vega maiden flight,” said Stefano Bianchi, Head of the Vega Programme at ESA.


About Vega

Vega is a single body launcher composed of three solid-propellant stages and a liquid-propellant upper module. It is approximately 30 metres high, and weighs a total of 137 tonnes at lift off. Vega's reference launch capacity is to carry a 1500 kg payload into a 700 km-altitude polar orbit, but the launcher is also designed to serve a wide range of scientific and Earth observation missions.

Source: ESA - News