Vega (rocket)
![]() Vega's VV05 before liftoff withSentinel-2A | |
Function | Small-lift launch vehicle |
---|---|
Manufacturer | Avio |
Country of origin | European multi-national[a] |
Cost per launch | US$37 million |
Size | |
Height | 30 m (98 ft) |
Diameter | 3 m (9.8 ft) |
Mass | 137,000 kg (302,000 lb) |
Stages | 4 |
Capacity | |
Payload topolar orbit | |
Altitude | 700 km (430 mi) |
Orbital inclination | 90° |
Mass | 1,430 kg (3,150 lb) |
Payload toelliptic orbit | |
Altitude | 1,500 km × 200 km (930 mi × 120 mi) |
Orbital inclination | 5.4° |
Mass | 1,963 kg (4,328 lb) |
Payload toSSO | |
Altitude | 400 km (250 mi) |
Mass | 1,450 kg (3,200 lb) |
Associated rockets | |
Derivative work | Vega C |
Comparable | |
Launch history | |
Status | Active, retiring |
Launch sites | Guiana Space Centre,ELV |
Total launches | 21 |
Success(es) | 19 |
Failure(s) | 2 |
First flight | 13 February 2012 (multiple payloads)[1] |
Last flight | 9 October 2023 (THEOS-2and others) |
First stage –P80[2][3][4] | |
Height | 11.7 m (38 ft) |
Diameter | 3 m (9.8 ft) |
Empty mass | 7,330 kg (16,160 lb) |
Gross mass | 95,695 kg (210,971 lb) |
Maximum thrust | 2,261 kN (508,000 lbf) |
Specific impulse | 280 s (2.7 km/s) |
Burn time | 107 seconds |
Propellant | HTPB/AP |
Second stage –Zefiro 23 | |
Height | 8.39 m (27.5 ft) |
Diameter | 1.9 m (6 ft 3 in) |
Empty mass | 2,850 kg (6,280 lb) |
Gross mass | 28,850 kg (63,600 lb) |
Maximum thrust | 871 kN (196,000 lbf) |
Specific impulse | 287.5 s (2.819 km/s) |
Burn time | 71.6 seconds |
Propellant | HTPB/AP[5] |
Third stage –Zefiro 9 | |
Height | 4.12 m (13.5 ft) |
Diameter | 1.9 m (6 ft 3 in) |
Empty mass | 1,315 kg (2,899 lb) |
Gross mass | 11,815 kg (26,048 lb) |
Maximum thrust | 260 kN (58,000 lbf) |
Specific impulse | 296 s (2.90 km/s) |
Burn time | 117 seconds |
Propellant | HTPB/AP[6] |
Fourth stage – AVUM | |
Height | 1.7 m (5 ft 7 in) |
Diameter | 1.9 m (6 ft 3 in) |
Empty mass | 147 kg (324 lb) |
Gross mass | 697 kg (1,537 lb) |
Powered by | 1 ×RD-843[7](RD-868P)[8] |
Maximum thrust | 2.42 kN (540 lbf) |
Specific impulse | 315.5 s (3.094 km/s) |
Burn time | 317 seconds |
Propellant | UDMH/N2O4 |
Vega(Italian:Vettore Europeo di Generazione Avanzata,French:Vecteur européen de génération avancée,lit. 'Vector European Generation Advanced')[9]is an expendablesmall-lift launch vehicle operated byArianespace,produced byAvio,and jointly developed by theItalian Space Agency(ASI) and theEuropean Space Agency(ESA). Development began in 1998 and the first launch took place from theGuiana Space Centreon 13 February 2012.[4]It is the 8th most launchedsmall lift launch vehiclein history. The final flight of the rocket is scheduled for September 2024, after which the vehicle will be replaced by the improvedVega C,already in use.
It is designed to launch small payloads, 300 to 2,500 kilograms (660 to 5,510 lb)satellitesfor scientific andEarth observationmissions topolarandlow Earthorbits.[10]The reference Vega mission is a polar orbit bringing a spacecraft of 1,500 kg (3,300 lb) to an altitude of 700 kilometres (430 mi).
The rocket, named afterVega,thebrightest starin the constellationLyra,[11]is a single-body launcher (no strap-on boosters) with threesolid rocketstages: theP80first stage, the Zefiro 23 second stage, and the Zefiro 9 third stage. The upper module is aliquid rocketcalled AVUM. The improved version of the P80 stage, theP120C,will also be used as the side boosters of theAriane 6.Italyis the leading contributor to the Vega program (65%), followed byFrance(13%).[12]Other participants includeSpain,Belgium,theNetherlands,SwitzerlandandSweden.[13]
Development
[edit]Background
[edit]During the mid-1990s, French firmsAérospatialeand SEP, along with Italian firmBombrini-Parodi-Delfino(BPD), commenced discussions on the development of a proposed Ariane Complementary Launcher (ACL). Around the same time, Italy began to champion the concept of a new solid-propellant satellite launcher.[14]This proposed launcher, dubbedVega,was promoted as functioning to expand the range of European launch capabilities; Vega would be capable of launching a 1000 kg payload into a 700 km polar orbit. From the onset, the first of three stages would be based on the solid booster of the existingAriane 5expendable launch system while the second and third stages would make use of the in-development Zefiro rocket motor.[15][16]
However, it was recognised to be a costly project and thus difficult for Italy alone to finance; accordingly, international partners were sought early on in order to proceed with development.[14]In April 1998, it was publicly stated that the Vega programme was dependent upon the securing of roughly ECU70 million of industrial investment, as well as the availability of around ECU350 million of funding that had been requested from interested member states of theEuropean Space Agency(ESA), led by France and Italy.[17]During June 1998, it was announced that ministers from European Space Agency (ESA) member states had agreed to proceed with the first phase of the development programme for Vega; the participating members were France, Belgium, the Netherlands, Spain and Italy – the latter had assumed 55% of the burden for financing the programme.[18][16]
By September 1998, it was projected that, if fully funded, Vega would perform its first launch during 2002.[19]However, by early 1998, France was publicly showing displeasure in the programme, leading to disputes in its funding.[20][21]A new, higher-performance version of the Vega was proposed, but this failed to sufficiently satisfy France. In September 1999, France decided to withdraw from the Vega programme entirely, leading to fears for the future of the launcher.[22]In November 1999,European Space Agency(ESA) formally dropped Vega as an endorsed programme, a decision which was largely attributed to France's withdrawal; Italy declared that it would proceed regardless, and threatened to re-direct its allocated contributions for the further development of the Ariane 5 to meet the shortfall.[23][24]
Around 2000, an alternative use for the Vega was explored as a medium-class booster rocket to be used in conjunction with an improved, up-rated model of the Ariane 5 heavy launcher.[25]In October 2000, it was announced that France and Italy had settled their year-long dispute over the Vega programme; France and Italy agreed to provide 35% and 52%, respectively, of the financing towards the all-composite P80 booster for the Ariane 5 — work which would be included in the Vega programme.[26]In March 2001,FiatAvioand theItalian Space Agency(ASI) formed a new company, European Launch Vehicle (ELV), to assume responsibility for the majority of development work on the Vega programme.[27]By 2003, there was concerns thatEuropean Space Agency(ESA)'s recent adoption of the RussianSoyuzlauncher would directly compete with the in-development Vega; demands for such launchers had declined with a downturn in the mobile telecommunications satellite market and doubts over the EuropeanGalileosatellite navigationsystem.[28]
Programme launch
[edit]In March 2003, contracts for development of the Vega launcher were signed byEuropean Space Agency(ESA) andCentre national d'études spatiales(CNES), the French space agency; Italy provided 65% of funding while six additional nations contributed the remainder.[29]In May 2004, it was reported that a contract was signed between commercial operatorArianespaceand prime contractor ELV to perform vehicle integration atKourou,French Guiana.[30]In November 2004, construction commenced upon a new dedicated launch pad for the Vega launcher at Kourou, this included abunkerand a self-propelled structure to assist assembly of the stages; this site was built over the original launch pad for the retiredAriane 1launcher.[31][32]In September 2005, the successful completion of key tests on the Vega's solid rocket motor igniters, a key milestone, was reported.[33]
In November 2005,European Space Agency(ESA) declared its desire for the development and deployment of anelectric propulsion-poweredmodule to work in conjunction with the Vega launcher; this envisioned module would transfer payloads betweenlow Earth orbit(LEO) and ageostationary orbit(GEO).[34]During November 2005, it was reported that bothIsraelandIndiahad shown formal interest in the Vega programme.[35]In December 2005, the Vega launcher, along with the Ariane and Soyuz launchers, were endorsed as the recognised "first choice" platforms for ESA payloads.[36]On 19 December 2005, the first test firing of the Vega's third stage was completed successfully atSalto di Quirra,Sardinia.[37]For several years, further tests would be conducted at the Sardinia site.[38][39]Progress on Vega was delayed by the failure of one such test of the third stage on 28 March 2007.[40][41]
During January 2007,European Space Agency(ESA) announced that the agency was studying the use ofGlobal Positioning System(GPS) navigation in order to support launches of the Vega and Ariane.[42]At the 2009Paris Air Show,it was revealed that the adoption of more cost-effective engine to replace the upper stages of the Vega have been postponed due to a failure to reduce the overall costs of the launcher, making it much less worthwhile to pursue.[43]Despite this finding, efforts to improve the efficiency of the third stage continued.[44]At this point, the certification of all four stages of the Vega launch was anticipated to be achieved prior to the end of 2009, while the first launch was scheduled to take place during 2010.[45]The first flight was intended to be flown with a scientific payload, rather than a "dummy" placeholder;[46][47]but had intentionally avoided a costly commercial satellite.[48]By late 2010, the first flight had been delayed into 2011.[49]
Into flight
[edit]During October 2011, all major components of the first Vega rocket departed Avio'sColleferrofacility, nearRome,by sea for Kourou. At this point, the first launch was anticipated to occur during December 2011 or January 2012.[50][51]During early January 2012, it was reported that the launch date would slip into the following month.[47][52]On 13 February 2012, the first launch of the Vega rocket occurred for Kourou; it was reported as being an "apparently perfect flight".[53][54]
During mid-2011, it was postulated that an evolved 'Europeanised' upgrade of the Vega rocket could be developed in the medium-to-long term future.[55]Following the successful first launch, various improvements for the Vega were postulated. TheGerman Aerospace Center(DLR) was reportedly enthusiastic on the prospects of developing a European alternative to the Vega's final, fourth stage; however, it was widely believed that there should be no change to Vega hardware for roughly 10 years in order to consolidate operations and avoid unnecessary costs early on.[56]European Space Agency(ESA) was also keen to take advantage of potential commonalities between the Vega and the proposedAriane 6heavy launcher.[57]
Following on from the first launch, a further four flights were conducted under the vestiges of the VERTA programme (Vega Research and Technology Accompaniment), during which observation or scientific payloads were orbited while validating and readying the Vega rocket for more lucrative commercial operations.[58]The second launch, performed on 6 May 2013, which followed a considerably more demanding flight profile and carried the type's first commercial payload, was also successful.[59]In the aftermath of this second launch,European Space Agency(ESA) declared the Vega rocket to be "fully functional".[60]The lapse of more than one year between the inaugural flight and the second one was mainly due to the fact that the Italian manufacturer had to completely redevelop the Flight Control Software, due to the restrictions on French export control imposed on the software used on the first flight.[61]
Since entering commercial service, Arianespace markets Vega as a launch system tailored for missions topolarandSun-synchronousorbits.[62]During its qualification flight, Vega placed its main payload of 386.8 kg, theLARESsatellite, into a circular orbit at the altitude of 1450 km with aninclinationof 69.5°.[63]
Specifications
[edit]Stages
[edit]Stages[64][65] | Stage 1 P80 |
Stage 2 Zefiro 23 |
Stage 3 Zefiro 9 |
Stage 4 AVUM |
---|---|---|---|---|
Height | 11.7 m (38 ft 5 in) | 7.5 m (24 ft 7 in) | 3.5 m (11 ft 6 in) | 1.7 m (5 ft 7 in) |
Diameter | 3 m (9 ft 10 in) | 1.9 m (6 ft 3 in) | 1.9 m (6 ft 3 in) | 1.9 m (6 ft 3 in) |
Propellant type | Solid | Solid | Solid | Liquid |
Propellant mass | 88,000 kg (194,000 lb) | 24,000 kg (53,000 lb) | 10,500 kg (23,100 lb) | 550 kg (1,210 lb) |
Motor dry mass | 7,330 kg (16,160 lb) | 1,950 kg (4,300 lb) | 915 kg (2,017 lb) | 131 kg (289 lb) |
Motor case mass | 3,260 kg (7,190 lb) | 900 kg (2,000 lb) | 400 kg (880 lb) | 16 kg (35 lb) |
Average thrust | 2,200 kN (490,000 lbf) | 871 kN (196,000 lbf) | 260 kN (58,000 lbf) | 2.42 kN (540 lbf) |
Burn time | 110 s | 77 s | 120 s | 667 s |
Specific impulse | 280 s (2.7 km/s) | 287.5 s (2.819 km/s) | 296 s (2.90 km/s) | 315.5 s (3.094 km/s) |
Payload
[edit]Arianespacehad indicated that the Vega launcher is able to carry 1,500 kg (3,300 lb) to a circularpolar orbitat an altitude of 700 km (430 mi).[66]
The payload fairing of the Vega was designed and is manufactured byRUAG Spaceof Switzerland.[67]It has a diameter of 2.6 metres, a height of 7.8 metres and a mass of 400 kg. The cylindrical part of the fairing has an outer diameter 2.6 m and a height 3.5 m.[68]
Three solid motor stages
[edit]The first three stages are solid propellant engines produced byAvio,that is prime contractor for the Vega launcher through its company ELV.[69]
As of 2011[update],the design and production process of the three engine types intended for the three stages of Vega were planned to be verified in twoground-test firings— one for design evaluation and one in the final flight configuration.[70][71][needs update]
P80
[edit]The P80 is the first stage of VEGA, its name is derived from the design phase propellant weight of 80 tons that was later increased to 88 tons. The P80 includes athrust vector control(TVC) system, developed and made in Belgium bySABCA,consisting of two electromechanical actuators that operate a movable nozzle with flexible joint using lithium-ion batteries.[72]The 3 m diameter case is composed ofgraphite epoxyfilament woundcase and low density rubber is used for the internal insulation. Thenozzleis made of light low-cost carbon phenolic material; a consumable casing is used for the igniter. Thesolid propellantloaded has low binder content and highaluminiumpercentage (HTPB 1912).[73]
The first test firing of the P80 engine took place on 30 November 2006 inKourou,and the test was concluded successfully.[74]
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.[75]
The future version of the stage,P120C,also with its name derived from the design phase propellant weight of 120 tons, will increase the propellant mass to 141–143 tons.[76]
Zefiro 23
[edit]The development of the Zefiro motor was initiated byAvio,partially funded by the company and partially funded by a contract from theItalian Space Agency(ISA). A Zefiro 23 forms the second stage of Vega. Itscarbon-epoxycase isfilament-woundand its carbon phenolic nozzle includes acarbon-carbonthroat insert. The propellant loading is 23 tons.[72]
The Zefiro 23 second stage engine was first fired on 26 June 2006 atSalto di Quirra.This test was successful.[77]
The second test firing of the Zefiro 23 second stage engine took place on 27 March 2008 also at Salto di Quirra. This successful test qualified the rocket engine.[78]
Zefiro 9
[edit]The first engine completed was Zefiro 9, the third-stage engine. The first test firing was carried out on 20 December 2005, at theSalto di QuirraInter-force Test Range, on theMediterraneancoast in southeastSardinia.The test was a complete success.[79]
After a critical design review based on the completed first test firings,[80]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.[81]No public information is available for this sudden drop of internal pressure, and whether any flaws were present in the motor's design.
On 23 October 2008, an enhanced version of the Zefiro 9 with a modified nozzle design, the Zefiro 9-A, was successfully tested.[82]
On 28 April 2009, the final qualification test firing of Zefiro 9-A took place at the Salto di Quirra Interforce Test Range inSardinia,Italy.[83]
Attitude Vernier Upper Module (AVUM)
[edit]![](https://upload.wikimedia.org/wikipedia/commons/thumb/0/0f/Vega-C_upper_stage_shaker_test.jpg/220px-Vega-C_upper_stage_shaker_test.jpg)
The Attitude Vernier Upper Module (AVUM)upper stage,developed byAvio,has been designed to place the payload in the required orbit and to perform roll and attitude control functions. The AVUM consists of two modules: AVUM Propulsion Module (APM) and AVUM Avionics Module (AAM).[84]The propulsion module uses a Ukrainian-builtRD-843[7](RD-868P)[8]rocket engineliquid-fuel rocketburning pressure-fedUDMHandnitrogen tetroxideas propellants. The AVUM avionics module contains the main components of the avionics sub-system of the vehicle.[85]
Variants
[edit]There was a concept study for a new medium-size launcher based on Vega andAriane 5elements. This launcher would use an Ariane 5 P230 first stage, a Vega P80 second stage and an Ariane 5 third stage using either storable or cryogenic fuel.[72]
The future upgraded Vega (LYRA program) has exceeded the feasibility study and is planned to replace the current third and fourth stages with a single low cost LOX/Liquid methane stage with a newguidance system.The purpose of the program is to upgrade the performance by about 30% without significant price increase.[86]
On 14 February 2012, one day after the successful first launch of Vega, theGerman Aerospace Center(DLR) moved to be included in the program. Johann-Dietrich Wörner, at that time head ofDLR,saidGermanywanted to join the project. Germany would provide a replacement for the RD-843 engine on the AVUM fourth stage, currently made inUkraine.The Vega launcher manager stated that it will not fly in the near future because it takes some time to develop, but he confirmed it will be on agenda in the next meeting of ministers in late 2012. That way, all components of the rocket would be built inside theEuropean Union(EU), excluding theSwissmade ones.[13]
The revised Vega-C first stage, renamedP120C(Common), has been selected asboosterfor the first stage of the next generationAriane 6rocket atEuropean Space Agency(ESA) Council meeting at Ministerial level in December 2014.[87]
Avio is also considering a "Vega Light" that would omit the first stage of either the Vega-C or Vega-E and would be targeted at replenishing satellite constellations. The vehicle would be capable of launching between 250–300 kg or 400–500 kg depending on whether it was derived from a Vega-C or Vega-E, respectively.[88][89]
Vega C
[edit]Vega C is an evolution on the original Vega launcher to enable better launch performance and flexibility.[90]Development started following the December 2014 ESA Ministerial Council with the goal to meet the change in payload demands, both in regards to an increase in medium-sized institutional payloads, and to compete with cheaper launch providers.[91]
This new evolution incorporates various changes to the Vega stack. The first stageP80 motorwill be replaced with theP120C,the same booster due to be used on the upcomingAriane 6launcher, and the Zefiro 23 second stage will also be replaced with the Zefiro 40. The larger AVUM+ will replace the AVUM fourth stage, while the third Zefiro 9 stage will be carried over from the base version of the launcher.[90]
These modifications will enable new mission parameters using various payload adapters and upper stages. The new rocket will be able to carry dual payloads using the Vespa-C payload adapter, or a single large satellite in addition to smaller payloads using the Vampire and SMSS multiple payload dispenser. Orbital transfer capability is also available with the Vega Electrical Nudge Upper Stage, or VENUS.[92]
Return missions are also available using the reusableSpace Ridervehicle, currently in development by ESA and due to launch on a Vega-C no earlier than July 2025.
On 13 July 2022, Vega-C had its debut flight, during which it delivered theLARES 2and six other satellites to orbit.[93]This launch came as a way of filling the gap after the Russian rockets became unavailable due to theinvasion of Ukraine.[94]On 21 December 2022 (UTC), Vega-C suffered a launch failure due to an anomaly with the Zefiro 40 second stage resulting in the loss of two spacecraft for theAirbus Pléiades Neo Earth-imaging constellation.[95]
Following the failure, the next launch was delayed until late 2024 to allow the redesign of a rocket motor nozzle.[96]
Vega-E
[edit]The Vega E (or Vega Evolution) is a further evolution of the Vega-C with the Zefiro 9 and AVUM+ third and fourth stages replaced with a cryogenic upper stage powered byliquid oxygenandliquid methane.This variant offers even more flexibility than Vega-C, with the ability to deliver multiple satellites into different orbits on a single launch.[97]
As of March 2021[update]Avio is finalizing the development of the newM10methane engine used in the new upper stage. The engine design is the result of a collaboration between Avio andChemical Automatics Design Bureau(KBKhA) ended in 2014.[98]
Avio successfully conducted the first series of testing of theM10engine between May and July 2022[99]with the maiden flight of the Vega-E planned for 2027.[100]
Launch statistics
[edit]Launch history
[edit]Note: Date and time of start (as count-down zero, ignition or lift-off?) is listed inUTC.(Although local time atGuiana Space Centre(CSG) in Kourou,French Guiana,South AmericaisUTC–3.)
2012
[edit]Flight | Date / time (UTC)[101] | Rocket, Configuration |
Launch site | Payload | Payload mass | Orbit | Customer | Launch Outcome |
---|---|---|---|---|---|---|---|---|
VV01 | 13 February 2012 10:00:00 |
Vega | ELV | LARES•ALMASat-1•e-st@r•Goliat•MaSat-1•PW-Sat•ROBUSTA•UniCubeSat-GG•Xatcobeo | LEO | University of Bologna[102] | Success | |
First Vega launch;GeodeticandNanosatellite; |
2013
[edit]Flight | Date / time (UTC)[101] | Rocket, Configuration |
Launch site | Payload | Payload mass | Orbit | Customer | Launch Outcome |
---|---|---|---|---|---|---|---|---|
VV02 | 7 May 2013 02:06:31 |
Vega | ELV | PROBA-V•VNREDSat 1A•ESTCube-1 | 254.83 kg (561.8 lb)[103] | SSO | ESA •VAST• | Success |
First commercial launch;Earth observation satellite;[104][105] |
2014
[edit]Flight | Date / time (UTC)[101] | Rocket, Configuration |
Launch site | Payload | Payload mass | Orbit | Customer | Launch Outcome |
---|---|---|---|---|---|---|---|---|
VV03 | 30 April 2014 01:35:15 |
Vega | ELV | KazEOSat 1 | 830 kg (1,830 lb)[106] | SSO | KGS | Success |
Earth observation satellite[107] |
2015
[edit]Flight | Date / time (UTC) | Rocket, Configuration |
Launch site | Payload | Payload mass | Orbit | Customers | Launch Outcome |
---|---|---|---|---|---|---|---|---|
VV04 | 11 February 2015 13:40:00 |
Vega | ELV | IXV | 1,845 kg (4,068 lb)[108] | TAO | ESA | Success |
Reentrytechnology demonstration;IXV deployed into atransatmospheric orbit,AVUM briefly entered a low Earth orbit before performing targeted de-orbit.[109][110][111][112][113] | ||||||||
VV05 | 23 June 2015 01:51:58 |
Vega | ELV | Sentinel-2A | 1,130 kg (2,490 lb)[114] | SSO | ESA | Success |
Earth observation satellite[115][116][117][118] | ||||||||
VV06 | 3 December 2015 04:04:00 |
Vega | ELV | LISA Pathfinder | 1,906 kg (4,202 lb)[119] | Halo orbitEarth–Sun L1 | ESA / NASA | Success |
Technology demonstrator[120][121] |
2016
[edit]Flight | Date / time (UTC) | Rocket, Configuration |
Launch site | Payload | Payload mass | Orbit | Customers | Launch Outcome |
---|---|---|---|---|---|---|---|---|
VV07 | 16 September 2016 01:43:35 |
Vega | ELV | PeruSat-1 • 4Terra Bellasatellites | 870 kg (1,920 lb)[122] | SSO | Peruvian Armed Forces•Terra Bella | Success |
Reconnaissance satellite/ Earth observation satellite[123][124] | ||||||||
VV08 | 5 December 2016 13:51:44 |
Vega | ELV | Göktürk-1A | 1,060 kg (2,340 lb)[125] | SSO | Turkish Armed Forces | Success |
Earth observation satellite[126](IMINT,Reconnaissance) |
2017
[edit]Flight | Date / time (UTC) | Rocket, Configuration |
Launch site | Payload | Payload mass | Orbit | Customers | Launch Outcome |
---|---|---|---|---|---|---|---|---|
VV09 | 7 March 2017 01:49:24 |
Vega | ELV | Sentinel-2B | 1,130 kg (2,490 lb)[127] | SSO | ESA | Success |
Earth observation satellite[128][129] | ||||||||
VV10 | 2 August 2017 01:58:33 |
Vega | ELV | OPTSAT-3000•VENμS | 632 kg (1,393 lb)[130] | SSO | Italian Defense Ministry•ISA/CNES | Success |
IMINTEarth observation satellite[131] | ||||||||
VV11 | 8 November 2017 01:42:31 |
Vega | ELV | Mohammed VI-A(MN35-13A) | 1,110 kg (2,450 lb)[132] | SSO | Morocco | Success |
Earth observation satellite[133] |
2018
[edit]Flight | Date / time (UTC) | Rocket, Configuration |
Launch site | Payload | Payload mass | Orbit | Customers | Launch Outcome |
---|---|---|---|---|---|---|---|---|
VV12 | 22 August 2018 21:20:09[134] |
Vega | ELV | ADM-Aeolus[135][136][137] | 1,357 kg (2,992 lb)[138] | SSO | ESA | Success |
Weather satellite | ||||||||
VV13 | 21 November 2018 01:42:31[139] |
Vega | ELV | Mohammed VI-B(MN35-13B)[139] | 1,108 kg (2,443 lb)[140] | SSO | Morocco | Success |
Earth observation satellite |
2019
[edit]Flight | Date / time (UTC) | Rocket, Configuration |
Launch site | Payload | Payload mass | Orbit | Customers | Launch Outcome |
---|---|---|---|---|---|---|---|---|
VV14 | 22 March 2019 01:50:35[141] |
Vega | ELV | PRISMA[142] | 879 kg (1,938 lb)[143] | SSO | Italian Space Agency | Success |
Earth observation satellite | ||||||||
VV15 | 11 July 2019 01:53 |
Vega | ELV | Falcon Eye 1 | 1,197 kg (2,639 lb) | SSO | UAEAF[144] | Failure[145] |
IMINT(Reconnaissance)– TheVV15launch failure was possibly caused by a thermal protection design flaw on the second stage's forward dome area,[146]and led to reassignment of the FalconEye 2 launch.[147][148]This also led to the highest recorded amount (US$411.21 million) for an insurance claim for a satellite launch failure.[149] |
2020
[edit]Flight | Date / time (UTC) | Rocket, Configuration |
Launch site | Payload | Payload mass | Orbit | Customers | Launch Outcome |
---|---|---|---|---|---|---|---|---|
VV16 | 3 September 2020 01:51:10[150] |
Vega | ELV | SSMS PoC Flight,D-Orbit,[151]Spaceflight Industries,[152]SITAEL[153]andISISpace[154]microsatellitesandcubesats(53 satellites). | 756 kg (1,667 lb)[155] | SSO | Various | Success |
Technology demonstration:launch of the Small Satellites Mission Service Dispenser (SSMS Dispenser) Proof of Concept Flight.[156] | ||||||||
VV17 | 17 November 2020 01:52:20[157] |
Vega | ELV | SEOSat-IngenioandTARANIS[158][159] | 925 kg (2,039 lb) | SSO | Centre for the Development of Industrial Technology(CDTI) (Spain) and Centre national d'études spatiales (CNES),France | Failure[160] |
Earth observation satelliteandStudy of the atmosphere of the Earth.After ignition of the AVUM upper stage, a trajectory deviation caused failure. Satellites were valued at nearly US$400 million.[160]An assembly error (inverted control cable) was the suspected cause.[160] |
2021
[edit]Flight | Date / time (UTC) | Rocket, Configuration |
Launch site | Payload | Payload mass | Orbit | Customers | Launch Outcome |
---|---|---|---|---|---|---|---|---|
VV18 | 29 April 2021 01:50[161] |
Vega | ELV | Pléiades Neo 3• NorSat-3 • Bravo • ELO Alpha •Lemur-2× 2 | 1,278 kg (2,818 lb) | SSO | Airbus Defence and Space•NOSA• Aurora Insight •Eutelsat•Spire Global | Success |
Small Satellites Mission Service (SSMS) piggyback mission. | ||||||||
VV19 | 17 August 2021 01:47[162] |
Vega | ELV | Pléiades Neo 4• BRO-4 • LEDSAT • RADCUBE • SUNSTORM | 1,029 kg (2,269 lb) | SSO | Airbus Defence and Space• UnseenLabs •Sapienza University of Rome•ESA• C3S Hungary •Reaktor Space Lab | Success |
Small Satellites Mission Service (SSMS) piggyback mission. | ||||||||
VV20 | 16 November 2021 09:27:55[163] |
Vega | ELV | CERES 1/2/3 | 1,548 kg (3,413 lb) | Semi-synchronous orbit(SSO) – New orbit by Vega | CNES•DGA | Success |
SIGINTsatellites.[164] |
2022
[edit]Flight | Date / time (UTC) | Rocket, Configuration |
Launch site | Payload | Payload mass | Orbit | Customers | Launch Outcome |
---|---|---|---|---|---|---|---|---|
VV21 | 13 July 2022 13:13:17[165] |
Vega-C | ELV |
|
350 kg (770 lb) | MEO | Success | |
First flight of Vega-C | ||||||||
VV22 | 21 December 2022 01:47:31[166] |
Vega-C | ELV | Pléiades-Neo 5•Pléiades-Neo 6(VHR-2020 3/4) | 1,977 kg (4,359 lb) | SSO | Airbus Defence and Space | Failure |
Earth observation satellites[167]Failure due to loss of pressure of theZefiro 40second stage.[168] |
2023
[edit]Flight | Date / time (UTC) | Rocket, Configuration |
Launch site | Payload | Payload mass | Orbit | Customers | Launch Outcome |
---|---|---|---|---|---|---|---|---|
VV23 | 9 October 2023 01:36[169] |
Vega | ELV | SSO | Success | |||
Earth observation satellitesand Small Satellites Mission Service (SSMS) #5 rideshare mission with 10 cubesats. Two cubesats, ANSER-Leader and ESTCube-2, failed to separate from the payload adapter and likely burned in the atmosphere together with the adapter when it was deorbited.[170] |
Future launches
[edit]2024
[edit]Date / time (UTC)[101] | Rocket, Configuration |
Launch site | Payload | Orbit |
---|---|---|---|---|
4 September 2024 01:50[171] |
Vega | ELV | Sentinel-2C | SSO |
Final flight of the base Vega configuration. ThirdSentinel-2Earth observation satellite. | ||||
15 November 2024[172] | Vega-C | ELV | Sentinel-1C | SSO |
ThirdSentinel-1satellite. Return to flight for Vega-C following the VV22 launch failure.[173] | ||||
December 2024[174] | Vega-C | ELV | KOMPSAT-6(Arirang-6) | SSO |
Earth observation satellite. |
2025
[edit]Date / time (UTC) | Rocket, Configuration |
Launch site | Payload | Orbit |
---|---|---|---|---|
Q1 2025[175] | Vega-C | ELV | SSMS #9 | LEO |
SSMS #9 rideshare mission. Delayed due to the VV22 Vega-C launch failure.[173] | ||||
Q2 2025[175] | Vega-C | ELV | SSMS #7 | SSO |
SSMS #7 rideshare mission. | ||||
Q3 2025[176] | Vega-C[177] | ELV | Sentinel-3C | SSO |
ThirdSentinel-3Earth observation satellite.[178] | ||||
Q3 2025[179] | Vega-C | ELV | Space Rider | LEO |
Technology demonstration[180] | ||||
Q3 2025[175] | Vega-C | ELV | SSMS #13 | SSO |
SSMS #13 rideshare mission. | ||||
November 2025[181] | Vega-C | ELV | PLATiNO-2 /MAIA | SSO |
PLATiNO-2 will host the MAIA instrument payload. | ||||
Q4 2025[182] | Vega-C | ELV | IRIDE ×? | LEO |
First launch for the Italian IRIDEEarth observation satelliteconstellation. | ||||
Q4 2025[182] | Vega-C | ELV | IRIDE ×? | LEO |
Second launch for the Italian IRIDEEarth observation satelliteconstellation. | ||||
Q4 2025[183] | Vega-C | ELV | SMILE | HEO |
Joint Chinese-EuropeanEarth observation satellite. | ||||
2025[175] | Vega-C | ELV | SSMS #8 | SSO |
SSMS #8 rideshare mission. | ||||
2025[177] | Vega-C | ELV | Sentinel-1D | SSO |
FourthSentinel-1satellite. | ||||
2025[184] | Vega-C | ELV | BIOMASS | SSO |
Earth observation satellite.Part of theLiving Planet Programme. | ||||
TBD[185] | Vega-C | ELV | PLATiNO-1 | SSO |
Earth observation satellite. | ||||
2025[175] | Vega-C | ELV | SSMS #6 | SSO |
SSMS #6 rideshare mission. | ||||
2025[175] | Vega-C | ELV | SSMS #10 | SSO |
SSMS #10 rideshare mission. | ||||
2025[186] | Vega-C | ELV | CO3D × 4 | SSO |
Earth observation satellites | ||||
2025[187] | Vega-C | ELV | CSG-3 | SSO |
ThirdCOSMO-SkyMed2nd Generation satellite. | ||||
2025[188] | Vega-C | ELV | MicroCarb | SSO |
Earth observation satellite. | ||||
2025[189][190] | Vega-C[191] | ELV | SHALOM | SSO |
Joint Italian-Israelihyperspectral imagingsatellite. |
2026
[edit]Date / time (UTC) | Rocket, Configuration |
Launch site | Payload | Orbit |
---|---|---|---|---|
January 2026[192] | Vega-C | ELV | KOMPSAT-7(Arirang-7) | SSO |
Earth observation satellite[193][194] | ||||
Q2 2026[175] | Vega-C | ELV | SSMS #14 | SSO |
SSMS #14 rideshare mission. | ||||
Q3 2026[175] | Vega-C | ELV | SSMS #15 | LEO |
SSMS #15 rideshare mission to an equatorial orbit. | ||||
Q3 2026[175] | Vega-C | ELV | SSMS #16 | LEO |
SSMS #16 rideshare mission to an equatorial orbit. | ||||
Q4 2026[176] | Vega-C[177] | ELV | CO2M-A(Sentinel-7A) | SSO |
Copernicus Anthropogenic Carbon Dioxide Monitoring. Part of theCopernicus Programme. | ||||
2026[195] | Vega-C | ELV | ALTIUS,FLEX | SSO |
ALTIUS is an ozone observation satellite. FLEX is anEarth observation satelliteof theLiving Planet Programme. | ||||
2026[196] | Vega-C | ELV | ClearSpace-1 | LEO |
Space debrisremoval demo. | ||||
2026[197] | Vega-C | ELV | CSG-4 | SSO |
FourthCOSMO-SkyMed2nd Generation satellite. | ||||
2026[198] | Vega-C | ELV | EAGLE-1 | LEO |
Demonstrator satellite for the first European sovereign space-basedquantum key distributionsystem.[199] |
2027
[edit]Date / time (UTC) | Rocket, Configuration |
Launch site | Payload | Orbit |
---|---|---|---|---|
Q1 2027[176] | Vega-C[177] | ELV | CO2M-B(Sentinel-7B) | SSO |
Copernicus Anthropogenic Carbon Dioxide Monitoring. Part of theCopernicus Programme. | ||||
Q2 2027[175] | Vega-C | ELV | SSMS #17 | LEO |
SSMS #17 rideshare mission. | ||||
2027[200][201] | Vega-C[202] | ELV | FORUM | SSO |
Earth observation satellite.Part of theLiving Planet Programme. | ||||
2027[203] | Vega-E | ELV | LEO | |
Maiden flight of Vega-E. |
2028
[edit]Date / time (UTC) | Rocket, Configuration |
Launch site | Payload | Orbit |
---|---|---|---|---|
Q2 2028[175] | Vega-C | ELV | SSMS #18 | LEO |
SSMS #18 rideshare mission. | ||||
Q4 2028[176] | Vega-C[204] | ELV | CRISTAL(Sentinel-9) | Polar |
Copernicus Polar Ice and Snow Topography Altimeter. Part of theCopernicus Programme. | ||||
Q4 2028[175] | Vega-C | ELV | SSMS #19 | LEO |
SSMS #19 rideshare mission. | ||||
2028[176] | Vega-C[205] | ELV | Sentinel-3D | SSO |
FourthSentinel-3Earth observation satellite.[178] |
2029
[edit]Date / time (UTC) | Rocket, Configuration |
Launch site | Payload | Orbit |
---|---|---|---|---|
Q2 2029[175] | Vega-C | ELV | SSMS #20 | LEO |
SSMS #20 rideshare mission. | ||||
Q3 2029[176] | Vega-C[206] | ELV | CIMR-A(Sentinel-11A) | SSO |
Copernicus Imaging Microwave Radiometer. Part of theCopernicus Programme. | ||||
Q4 2029[175] | Vega-C | ELV | SSMS #21 | LEO |
SSMS #21 rideshare mission. | ||||
2029[206] | Vega-C | ELV | CHIME(Sentinel-10) | SSO |
Copernicus Hyperspectral Imaging Mission. Part of theCopernicus Programme. | ||||
2029[206] | Vega-C | ELV | LSTM(Sentinel-8) | SSO |
Copernicus Land Surface Temperature Monitoring. Part of theCopernicus Programme. |
2030
[edit]Date / time (UTC) | Rocket, Configuration |
Launch site | Payload | Orbit |
---|---|---|---|---|
2030[207] | Vega-C | ELV | TRUTHS | LEO |
Traceable Radiometry Underpinning Terrestrial- and Helio-Studies. |
Costs
[edit]Development costs for the Vega rocket totaled €710 million, with ESA spending an additional €400 million to sponsor five development flights between 2012 and 2014.[208]Estimates of commercial launch costs in 2012 were projected to be €32 million, including Arianespace's marketing and service costs, or €25 million for each rocket alone, assuming a launch rate of 2 per year. In 2012, the managing director of ELV estimated that if the sustained flight rate were to increase to four flights per year, the price of each individual launch vehicle could potentially decrease to €22 million.[209][needs update]In the event, by November 2020, Vega had never flown more than three flights in a single year, with an average flight rate of just under two launches per year.
"Our belief is that we can charge up to 20% more per launch than our biggest competitors and still win business because of the value we provide at the space center here and with Arianespace"
— Francesco De Pasquale, managing director of ELV SpA, 2012, SpaceNews[209]
Comparable rockets
[edit]- Delta II7420 (retired)
- Epsilon
- Firefly Alpha
- Minotaur IV
- Minotaur-C
- Rokot(retired)
- Soyuz-2-1v
- Polar Satellite Launch Vehicle
- List of Vega launches
See also
[edit]- Vega-C
- List of Vega launches
- Solid rocket
- Comparison of orbital launchers families
- Comparison of orbital launch systems
Notes
[edit]- ^The lead manufacturer is fromItaly,but the rocket has significant contributions from companies based inBelgium,France,Netherlands,Spain,SwitzerlandandUkraine.
References
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External links
[edit]![](https://upload.wikimedia.org/wikipedia/en/thumb/4/4a/Commons-logo.svg/30px-Commons-logo.svg.png)
- Vega launcher,European Space Agency
- ELV – European Launch Vehicle s.p.a.
- Vega Launcher, Avio
- First stone for Vega at Europe's Spaceport
- Vega brochure
- Vega Leaflet
- Vega Nozzle
- Telemetry Simulator of VEGA
- A star rocket is born(Television production). Euronews. 1 February 2012.Archivedfrom the original on 12 December 2021.Retrieved3 February2012.
- Vega's First Launch Campaign.European Space Agency. 31 January 2012.Archivedfrom the original on 12 December 2021.Retrieved3 February2012.