Esa Bulletin 135 - August 2008 45 Vega

The former ELA-1 Ariane-1 launch pad at Kourou has Stefano Bianchi, Renato Lafranconi & been transformed for Vega. The Mobile Gantry is in place and the site almost complete. In the background, an Michel Bonnet Ariane-5 is seen being moved to its launch site ELA-3 Vega Programme, Directorate of Launchers, ESRIN, Frascati, Italy

key element of the European launcher strategy for access to space, the Vega A small launcher is being preparing for its maiden flight in November 2009.

The development of Vega passed major milestones in 2007 and 2008, providing essential results in terms of test data and design consolidation. These will lead to the Qualification Flight from Europe’s Spaceport in French Guiana at the end of 2009. This will be an important step in the implementation of the European strategy in the launcher sector and the guarantee of access to space for Europe, as endorsed by the ESA Ministerial Council in 2003. The ex p l o i t ation of this new ESA developed launcher will widen the range of launch services offered by launchers developed and produced by European industry and will improve launch flexibility by providing a more adapted response for a wide range of European institutional space missions, as well as an optimised family of launchers to serve commercial market needs.

esa bulletin 135 - august 2008 45 Vega

key element of the European launcher strategy for access to space, the Vega A small launcher is being preparing for its maiden flight in November 2009.

esa bulletin 135 - august 2008 45 Launchers Vega

The Vega and VERTA Programmes to enlarge the qualification domain, The Vega launch system, curre n t ly sustaining its reliability, demonstrating developed by ESA, has an essential role its flexibility through various missions within the family of launchers that will and enhancing its affo rd ability fo r be operated by Arianespace at the future customers. European Spaceport in French Guiana The Vega and VERTA programmes (Centre Spatial Guyanais, CSG). It will a re funded by the fo l l ow i n g complement the European Ariane and p a r t i c i p ating states: Belgium, Fra n c e, the Russian Soyuz: Ariane is optimised I t a ly, The Netherl a n d s, Switze rl a n d , for larger spacecraft and missions to Spain and Sweden. Geostationary Transfer Orbit (GTO) as The programme is managed by an well as Earth gravity escape missions, Integrated Project Team composed of while Soyuz is suitable for medium staff from ESA, the Italian space agency satellites in GTO and heavy satellites in ASI and the French space ag e n c y Low Earth Orbit (LEO). CNES, based at ESRIN in Frascati, Vega is a four-stage launch vehicle Italy, for the launch vehicle and ground designed to cover a wide range of small segment, and at CNES-DLA in Evry, s atellite missions in LEO. The main France, for the P80 demonstrator. system re q u i re m e n t s, in terms of The industrial organisation is based payload mass and dimensions as well as Participation in the Vega and VERTA programmes on a prime contractor for each project: mission ra n g e, we re driven by the ELV (I) for the launch vehicle, AVIO (I) market projection showing a broad need with delegation to Europropulsion (I/F) of different missions as follows: In order to prepare the exploitation services for five ESA missions, wa s for the P80 demonstrator, and Vitrociset – Re f e rence: 1500 kg in polar circ u l a r p h a s e, the Vega Re s e a rch and decided by the participating states at the (I) for the ground segment. 700 km orbit, Technology Accompaniment (VERTA) ESA Ministerial Council in December – Mission range: inclination 5° to sun- p rog ra m m e, including the launch 2005. This programme has the objective The Vega Launcher s y n c h ronous orbit, LEO and small- The Vega launcher is a single-body to-medium payload mass ra n g e, fro m vehicle composed of three solid-rocket m i c ro and mini-satellites up to ESA’s family of launchers: Vega, Soyuz, Ariane-5 and Ariane-5 ECA motor (SRM) stages (P80, Zefiro-23 and 2.5-tonne sat e l l i t e s. Z e f i ro-9), a liquid-propulsion upper In 2010–15, the addressable market stage (Attitude Vernier Upper Module, consists of five to seven satellites a year AVUM) and a fairing. At lift-off, the with a mass greater than 250 kg and launcher is 30.2 m high and weighs c o m p at i ble with the Vega re f e re n c e 139 tonnes. capability. This fully consolidates the To minimise risks and costs, the planned launch rate of two launches per development has been based on a mix of year as a minimum. we l l - p roven technolog i e s, benefiting The Vega programme is composed of f rom synergy with Ariane-5 three ESA optional programmes (the development and with new technologies Small Launcher programme, the P80 aimed at reaching low recurring cost d e m o n s t rator prog ramme and an objectives. The choice of solid-rocket additional programme slice, decided at motors was driven mainly by the end of 2007) organised into three demonstrated high reliability on Ariane p rojects: the launch ve h i c l e, the P80 programmes and by low development (first stage solid-rocket motor) and the and recurrent costs. ground segment. The three solid-propellant stag e s The Vega launch system includes also perform the main ascent phase while the the dedicated launcher infrastructure at fourth stage compensates for the solid- CSG and the worldwide ground station p ropulsion perfo r mance scat t e r i n g , network necessary to launch a payload circularises the orbit and executes the and to place it into the required orbit, de-orbiting manoeuvres. respecting the specified environment for The diameter of the first stage has the payload, the safety and operational been set to 3 m in order to exploit fully Vega launcher configuration constraints. the synergies with alre a dy ex i s t i n g and dimensions Ariane facilities for casting and

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and execution means, data pro c e s s i n g The fo rmer Ariane-1 plat fo r m P80 Z23 Z9 and data commu n i c ation needed by ( bu n ker) is being refurbished and the flight control function (during upgraded for Vega. The launch pad Overall length (mm) 10 791 7585 3953 p r e-launch and flight mission i t s e l f is equipped with seve ral pipe Outer diameter (mm) 3003 1904 1907 p h a s e s ) ; n e t wo rks which fulfil the diff e re n t – the electrical safeguard subsystem, functions required, e.g. pressurisation, Propellant mass (kg) 87 733 23 823 10 570 consisting of all the equipment fo r cooling, ve n t i l ation, flushing and Inert mass (kg) 7030 1951 915 p ower generation, reception, pro - propellants loading. cessing and transmission to gro u n d The Upper Composite assembly and Burn time (s) 110 77 118 needed by the safety functions; checks will be done inside the payload – the telemetry subsystem, including all integration facilities at CSG (Ensemble Vacuum specific impulse (s) 280 288 296 the means to acquire and process the de Pré p a rat ion des Charges Utiles, Nozzle expansion ratio 16 27 72.5 telemetry monitoring functions, and EPCU). t ransmit to the gro u n d . The Vega Control Bench facilities will SRM nominal characteristics and performances In order to reduce as much as possible be located in the Centre De Lancement the development and recurring costs, the (Launch Centre) No. 3 (next to that for Vega avionics system is based on the use Ariane-5). Characteristics and performances of existing hardware and/or components AVUM stage dry mass (kg) 615 f rom Ariane and other ESA pro - Vega Development Status grammes. As an example, the Vega on- Launch vehicle Propellant loading (kg) 577 b o a rd computer (OBC) is based on System activities in 2007 were devoted Pressuring (GHe) gas loading (kg) 4.1 existing blocks and components from to the consolidation of the launch ESA satellite programmes. system design in the frame of the Vega Main engine thrust (N) 2450 System Critical Design Review activi- The P80 firing tests at the the Booster Test Stand at the Centre Spatial Guyanais in December 2007 The Ground Segment ties, allowing the start the qualification LPS total impulse (kN s) 1634 As with Ariane-4, the Vega launcher is loop activities in December. Restart capability 5 assembled and tested on its launch pad. In parallel, the development activities i n t e g rat ion. The P80 is the larg e s t Avionics functions are distribu t e d The launcher preparation takes place at equipment and subsystem levels have AVUM nominal characteristics and performances monolithic solid-rocket motor with a among hardwa re items and onboard inside a Mobile Gantry, housing all the allowed the completion of most of the filament winding CFRP motor case ever s o f t wa re. They are split into thre e Ground Support Equipment needed to critical design reviews. For some of the developed in the world. subsystems: assemble and check the launcher, which elements, like the fairing, the inter-stage The Vega Upper Composite electro- A few months later, in March 2008, at The fourth stage (AVUM) includes a – the guidance, nav i g ation and contro l is moved back a few hours before the 0/1, the ignition and separation pyro- m agnetic compatibility tests we r e the Italian Air Force Salto di Quirra b i p ropellant (NTO/UDMH) liquid- subsystem, grouping all acquisition launch. chains, the AVUM structure, the On- completed successfully in Colleferro (I) Range (Sardinia), the Zefiro-23 solid- propulsion system (LPS) that provides Board Computer and the safety units, during summer 2007, and in INTA (E) rocket motor – the second stage – also the necessary velocity changes fo r Qualification Reviews have already been for the final part of the conducted and completed its functional qualificat i o n reaching the final launcher orbit, and a performed. radiated susceptibility tests at the end of with a successful second test-firing. m o n o p ropellant (hyd razine) Roll and Testing activities have been ve r y 2007/early 2008. The qualification firing test of the Attitude Control System (fulfilling the intense too. The Upper Composite The qualification of the avionics has Zefiro-9 solid-rocket motor took place main functions of roll control during Mechanical model (UCMEC) under- made significant steps ahead with the set in March 2007, but failed with the flight, attitude control during coasting went vibration and acoustic testing at up of the ‘hardware in the loop’ facility, ejection of the nozzle after 35 seconds of phases, attitude recovery during second- the ESTEC Test Centre from summer now nearly finished, and the completion operating time. An inquiry board was s t age separation, payload pointing 2006 until the beginning of October. of the first validation campaigns of the put in place, and pointed some manoeuvre and orbit control for the The third and fourth stage separation s a f e g u a rd subsystem (SAS) and weaknesses in the design of the nozzle collision avoidance manoeuvre). and fairing horizontal separation system communication subsystem. and in manufacturing quality on some The Upper Composite, composed by (HSS) tests have been perfo r med, in The P80 solid-rocket motor – the first of its components. Intense work was the payload adapter, the payload and EADS-CASA facilities in Spain, in s t age – successfully completed its made by Avio teams in order to recover the fairing is mated on the top of the December 2006 and February 2007 q u a l i f i c ation firing test in December the situation, with a complete material fourth stage. re s p e c t ive ly. During November 2007, 2007, one year after the test-firing of the characterisation campaign (in particular In a single launch configuration, Vega the chara c t e r i s ation of the launch d evelopment model, confirming the of the carbon-phenolic (C-Ph) materials provides a minimum volume allocated vehicle bending modes and structural predicted performances and behaviour. used in the insulators of the carbon- to the payload consisting of a damping was carried out at IABG (D) Due to its size, the P80 firing tests are carbon nozzle throat, operating at up to Characterisation of launch cylindrical volume of 2.35 m diameter vehicle bending modes and with the integration of all the launch performed at the Booster Test Stand 2000°C), redesign of the nozzle, and and 3.5 m height plus a frustum volume structural damping at IABG vehicle subassemblies except the first (Bâtiment d’Essais des Accélérateurs à i m p rovement in the manu f a c t u r i n g of 2.8 m height. in Germany (ELV) stage (P80 plus inter-stage 0/1). Poudre, BEAP) at CSG. process and then quality of the C-Ph

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Ground Segment p o r t ation to Ko u rou , storag e, inte- f r ame due to Earth’s angular The Vega ground segment has entered in gration on the launch table and the final momentum (or ‘Lense-Thirring effect’) its final phase with the completion of preparation of the launch vehicle as for and a high precision test of E a r t h ' s the detailed design of the va r i o u s flight, which includes the pro p e l l a n t gravitomagnetic field. Gravitomagnetic subsystems (mechanical, fluid and loading and the va l i d ation of t h e field and inertial frame drag are control centre). countdown phase. p r edictions of E i n s t e i n’s theory of At CSG, the civil wo rks of A dedicated Integrated Operat i o n s General Relativity. refurbishment of the bu n ker and Team has been set up to manage this The secondary payloads of t h e integration of the Mobile Gantry main Combined Test Campaign, taking maiden flight are educational micro - structure have been completed as well as advantage of the cooperation between satellites. the installation of equipments fo r the different players and securing at the h e ating, ve n t i l ation and air condi- same time the continuity of technical From Development to Exploitation tioning. The launch table has been competences through the diff e re n t For a smooth transition betwe e n integrated in its position, and will be phases of realisation and validation of d e velopment and ex p l o i t ation, the soon completed with the upper and p roducts up to the integration and VERTA programme will undertake five l owe r pallets. The umbilical mast is launch campaigns. Specialists fro m fl exi bility demonstration fl i g h t s, being erected in the launch area, in industrial contractors, support services p r i m a r i l y for ESA user missions. parallel with the integration of piping and the future operator Arianespace are Different ESA user mission candidates Mobile Gantry integration activities in CSG (Vitrociset) for fluid installation. involved under the coordination of the a r e alre a dy identified for these five Fluid panels factory acceptance has Vega Integrated Project Team. launches: been completed in Europe and they will After completion of the combined – ADM-Aeolus Earth observat i o n insulators. Most of these improvements the P80 and Zefiro tests, simu l at i n g be shipped to Kourou and connected to tests and Ground Qualification Review, mission, weighing around 1400 kg, we re applied on the nozzle of the worst-case manoeuvre s, and the the networks on the launch pad. the Flight Readiness Review will enable to be placed in a sun-synchronous Zefiro-23 qualification model and the performance was satisfactory. The Vega Control Centre (CCV), fully the start of the Qualification Flight orbit at about 400 km altitude; nozzle expertise after its successful firing For the liquid-propulsion subsystem – d eve loped and tested at the gro u n d campaign that will complete the – SWARM Earth observation mission, test confirmed the soundness of t h e the fo u r t h - s t age main engine – derive d segment prime contractor premises with preparation for the maiden flight. The comprising a constellation of three modifications. f rom the Ukrainian RD-869 engine a first release of software, has been Launch Readiness Review will give the s atellites in near-polar orbits, Taking adva n t age of the schedule ( Yu z h n oye) has alre a dy successfully shipped to the launch site. This release green light for the maiden flight, and between 450 and 550 km altitude; shift because of the redesign of the u n d e rgone seve ral test campaigns with will be used to start the ground segment this will be fo l l owed by a detailed – LISA Pathfinder science mission, Zefiro-9 nozzle, the project decided to t wo qualification models. The firing test integrated tests phase. Further releases exploitation of the flight results and by weighing about 1900 kg, with an increase the Zefiro-9 performance with at subsystems level (complete liquid are foreseen to cover late changes. the Flight Qualification Review. o p e rational orbit around the first an overloading of propellant (by 560 p ropulsion subsystem in the fl i g h t The next important milestone for the Earth-Sun Lagrange point (L1) after kg), allowing and improvement in c o n f i g u ration) is under pre p a ration at Vega ground segment is the Te s t The Qualification Flight a transfer trajectory from a low launcher payload cap ability of m o re the P2 test stand in Lampoldshausen (D) Readiness Review for the integrated test The mission for the Qualification Flight Earth parking orbit; than 60 kg. Following a review of the and the test campaign will start in phase under the responsibility of the has been defined to take into account – Proba-3, a formation-flying cluster impact at motor and system levels, the summer 2008. This will be the final step industrial prime contractor and closely d i ff e rent targets: mitigation of r i s k s of two mini-satellites, with a highly i m p l e m e n t ati on of this modificat i o n to demonstrate the liquid-pro p u l s i o n followed by ESA/IPT with a dedicated i n h e rent to the first flight, re p re s e n - elliptical final orbit; was endorsed through the System system suitability for the Qualificat i o n team on site. The closure of this test t at ive ness of the mission within the – ESA IXV demonstrator for re-entry Critical Design Review. Flight. The manufac-turing, assembly phase will allow pronouncing the flight qualification domain, compliance ap p l i c at i o n s, weighing around Because of these significant changes and integration of the units for the technical qualification of the Ve g a with gro u n d / flight safety and pro - 1850 kg, to be de-orbited by the Vega in the third-stage motor configuration Q u a l i f i c ation Flight have alre a dy started, ground segment. grammatic constraints. upper stage before starting its re- (now named Zefiro-9A), two firing tests a c c o rding to their qualification stat u s. In particular, due to the larg e r entry phase at 120 km altitude. a re still needed to demonstrate the The focus in 2008 on the launch Launch System uncertainties in a first flight, specific For the first VERTA flight, scheduled q u a l i f i c ati on. They are scheduled in vehicle side will be the closure of the Activities at launch system level are now constraints are introduced to limit the six months after the maiden flight, ESA October 2008 and February 2009. major actions resulting from the focused at the pre p a rat ion of t h e risks safetywise. Hence the pay l o a d will issue an international Announce- Not only do solid-rocket motor firing development activities and reviews, the Combined Test Campaign. This will be mass has been reduced for this flight. ment of Opportunity (AO). The tests verify the correct overall behaviour completion of all the qualificat i o n the major step of the launch system The main passenger of the maiden response to the AO will be assessed by of the Vega motors and demonstrate rev i ews at equipment and subsystem development, being the first time that flight is the LARES ex p e r i m e n t ESA, with the participation of that the ballistic performances comply levels and the acceptance of the flight the launcher (a representative mock-up) developed by ASI. This is a satellite Arianespace, and building upon such an with the system requirements, but they u n i t s, as well as of course the and the ground segment will meet l a s e r- ranging experiment, completely assessment, in a second step, a Call(s) also contribute to the Thrust Vector preparation of the ground qualification together. passive with no sensors or on-board for Proposals will be published, and the Control (TVC) subsystems qualification review of the launch system, scheduled These tests will allow the validation of electronics. The main scientific objective payload(s) for the first VERTA flight as well. Large amplitude movements of to start in the first quarter of 2009, and all pro c e s s e s, from the delivery of o f the LARES mission is the AVUM and fairing at ESTEC for upper-composite mechanical tests will be selected. e the TVC system were executed during the preparation for the maiden flight. subassemblies in Europe, their trans- measurement of the dragging of inertial (ELV)

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