Ariane 5 ES with ATV-4 on board on its way to the launch pad
|Function||Heavy launch vehicle|
|Manufacturer||Airbus Defence and Space for
ESA and Arianespace
|Country of origin||Europe|
|Height||46–52 metres (151–171 ft)|
|Diameter||5.4 metres (18 ft)|
|Mass||777,000 kilograms (1,713,000 lb)|
|Payload to LEO||G: 16,000 kg
ES: 21,000 kg
|G: 6,200 kg
G+: 6,950 kg
GS: 6,100 kg
ECA: 10,500 kg
|Launch sites||ELA-3, Guiana Space Centre|
(G: 16, G+: 3, GS: 6)
(ECA: 44, ES: 5)
(G: 13, G+: 3, GS: 6)
(ECA: 43, ES: 5)
|Failures||2 (G: 1, ECA: 1)|
|Partial failures||2 (G)|
|First flight||G: 4 June 1996
G+: 2 March 2004
GS: 11 August 2005
ECA: 11 December 2002
ES: 9 March 2008
|Last flight||G: 27 September 2003
G+: 18 December 2004
GS: 18 December 2009
Automated Transfer Vehicle
Herschel Space Observatory
|Boosters (Stage 0) - P230|
|Thrust||6,470 kN each (1,450,000 lbf)|
|Specific impulse||275 seconds (2.70 km/s)|
|Burn time||129 seconds|
|First stage (Ariane 5G)|
|Thrust||1,114 kN (250,000 lbf)|
|Specific impulse||430 seconds (4.2 km/s)|
|Burn time||589 seconds|
|First stage (Ariane 5 ECA) - EPC (Étage Principal Cryotechnique, Cryogenic main stage)|
|Engines||1 Vulcain 2|
|Thrust||1,340 kN (301,000 lbf)|
|Specific impulse||431 seconds (4.23 km/s)|
|Burn time||650 seconds|
|Second stage (Ariane 5G, Ariane 5ES)|
|Thrust||27.4 kN (6,160 lbf)|
|Specific impulse||324 seconds (3.18 km/s)|
|Burn time||1,100 seconds|
|Second stage (Ariane 5 ECA)|
|Thrust||64.7 kN (14,500 lbf)|
|Specific impulse||446 seconds (4.37 km/s)|
|Burn time||960 seconds|
Ariane 5 is a European rocket that is a part of the Ariane rocket family, an expendable launch system used to deliver payloads into geostationary transfer orbit (GTO) or low Earth orbit (LEO). Ariane 5 rockets are manufactured under the authority of the European Space Agency (ESA) and the Centre National d'Etudes Spatiales (CNES). Airbus Defence and Space is the prime contractor for the vehicles, leading a consortium of sub-contractors. Ariane 5 is operated and marketed by Arianespace as part of the Ariane programme. Astrium builds the rockets in Europe and Arianespace launches them from the Guiana Space Centre in French Guiana.
Ariane 5 succeeded Ariane 4, but was not derived from it directly. Ariane 5 has been refined since the first launch in successive versions, "G", "G+", "GS", "ECA", and most recently, "ES". ESA originally designed Ariane 5 to launch the manned mini shuttle Hermes, and thus intended it to be "human rated" from the beginning.
Two satellites can be mounted using a SYLDA carrier (SYstème de Lancement Double Ariane). Three main satellites are possible depending on size using SPELTRA (Structure Porteuse Externe Lancement TRiple Ariane). Up to eight secondary payloads, usually small experiment packages or minisatellites, can be carried with an ASAP (Ariane Structure for Auxiliary Payloads) platform.
By mid-2007, Arianespace has ordered a total of 99 Ariane 5 launchers from Astrium. The first batch ordered in 1995 consisted of 14 launchers, while the second—P2—batch ordered in 1999 consisted of 20 launchers. A third—PA—batch consisting of 25 ECA and 5 ES launchers was ordered in 2004. The latest batch ordered in mid-2007 consist of another 35 ECA launchers. Through these orders, the Ariane 5 will be the workhorse of Arianespace at least through 2015.
Cryogenic main stage
Ariane 5’s cryogenic H158 main stage (H173 for Ariane 5 ECA) is called the EPC (Étage Principal Cryotechnique—Cryotechnic Main Stage). It consists of a large tank 30.5 metres high with two compartments, one for 130 tonnes of liquid oxygen and one for 25 tonnes of liquid hydrogen, and a Vulcain engine at the base with thrust of 115 tonnes-force (1.13 meganewtons). This part of the first stage weighs about 15 tonnes when empty.
Attached to the sides are two solid rocket boosters (SRBs or EAPs from the French Étages d’Accélération à Poudre), P238 (P241 for Ariane 5 ECA), each weighing about 277 tonnes full. Each delivers a thrust of about 630 tonnes-force (6.2 MN). These SRBs are usually allowed to sink to the bottom of the ocean, but like the Space Shuttle Solid Rocket Boosters they can be recovered with parachutes, and this is occasionally done for post-flight analysis. (Unlike Space Shuttle SRBs Ariane 5 boosters are not reused.) The most recent attempt was for the first Ariane 5 ECA mission. One of the two boosters was successfully recovered and returned to the Guiana Space Center for analysis. Prior to that mission, the last such recovery and testing was done in 2003.
The second stage is on top of the main stage and below the payload. The Ariane 5G used the EPS (Étage à Propergols Stockables—Storable Propellant Stage), which is fueled by monomethylhydrazine (MMH) and nitrogen tetroxide, whereas the Ariane 5 ECA uses the ESC (Étage Supérieur Cryotechnique—Cryogenic Upper Stage), which is fueled by liquid hydrogen and liquid oxygen. Ariane 5G+ used and Ariane 5 GS and ES use an improved EPS upper stage.
The EPS upper stage is capable of re-ignition, which has been demonstrated four times. The first demonstration occurred during flight V26, which was launched on 5 October 2007. This was purely to test the engine, and occurred after the payloads had been deployed. The first operational use of restart capability as part of a mission, came on 9 March 2008, when two burns were made to deploy the first Automated Transfer Vehicle into a circular parking orbit, followed by a third burn after ATV deployment to de-orbit the stage. The exact procedure has since been used at least two more times on subsequent ATVs.
The payload and all upper stages are covered at launch by a fairing, which splits off once sufficient altitude has been reached (typically above 150 km).
|G||The original version is dubbed Ariane 5 G (Generic) with a launch mass of 737 tonnes. Its payload capability to geostationary transfer orbit (GTO) was initially specified as 5,970 kg (13,160 lb), but was increased after the qualification flights to 6,200 kg (13,700 lb).|
|G+||The Ariane 5 G+ had an improved second stage, with a GTO capacity of 6,950 kg (15,320 lb) for a single payload. It flew three times in 2004.|
|GS||It was replaced in 2005 by the Ariane 5 GS, with the same EAP boosters as the ECA and ES variants and a first stage based on the later Evolution EPC, but with the original tank volumes and a Vulcain 1B engine. The GS was introduced following the failure of the first Ariane 5 ECA flight—since all the vehicles then in production were ECA versions, it was decided to modify some of them to use the original Vulcain engine while the failure was investigated. It can carry a single payload of 6,100 kg (13,400 lb) to GTO. The last of 6 Ariane 5 GS rockets was launched in 2009.|
|ECA||The Ariane 5 ECA (Evolution Cryotechnique type A) has a GTO launch capacity of 10,000 kg (22,000 lb) for dual payloads or 10,500 kg (23,100 lb) for a single payload. This variant uses a new Vulcain 2 first-stage engine, and an ESC-A (Etage Supérieur Cryogénique-A) second stage, powered by an HM-7B engine, weighing 2,100 kg (4,600 lb) and carrying 14,000 kg (31,000 lb) of cryogenic propellant. The second stage uses the liquid oxygen tank and lower structure from the Ariane 4's H10 third stage, mated to a new liquid hydrogen tank. The revised Vulcain has a longer, more efficient nozzle with more efficient flow cycle and denser propellant ratio. The new ratio demanded length modifications to the first-stage tanks. Also, the solid EAP casings have been lightened with new welds, and packed with more propellant. The ESC-A cryogenic second stage does not improve the performance to Low Earth orbit compared to Ariane 5G, and for this reason the Ariane 5 ECA will not be used to launch the Automated Transfer Vehicle (ATV).|
|ES||The Ariane 5 ES (Evolution Storable) is used to launch the Automated Transfer Vehicle (ATV) into a 260 km circular low Earth orbit inclined at 51.6°. It includes all the performance improvements of Ariane 5 ECA on EPC (Etage Principal Cryogénique—main stage) and EAP (Etage d'Accélération à Poudre—solid rocket booster) stages while the second stage is the EPS (Etage à Propergols Stockable) used on Ariane 5 GS variants. It is estimated that the Ariane 5 ES can put up to 21,000 kg (46,000 lb) in LEO. The first such launch occurred at 04:03 GMT on 9 March 2008.|
|ES Galileo||The Ariane 5 ES Galileo is a modification of the standard ES version able to launch four Galileo satellites at a time into 23,000 km circular orbits and due to enter service in the latter half of 2014. It will feature modifications to the payload fairing and payload delivery system to grant the ability to launch four satellites into unique orbits in a single launch. The variant was approved in February 2012 and alongside Soyuz launching two at a time will deliver the second Galileo constellation of 16 satellites during 2014 and 2015.|
|ME||The Ariane 5 ME (Mid-life Evolution) is currently under development. First launch scheduled for 2018.|
Ariane 5 ME
The Ariane 5 ME (Mid-life Evolution) is currently in development and will replace Ariane 5 ECA and Ariane 5 ES. With first flight planned for 2018, it will become ESA's principal launcher until the arrival of the new Ariane 6 version.
The Ariane 5 ME uses a new upper stage, with increased propellant volume, powered by the new Vinci engine. Unlike the current engine, it can restart several times, allowing for insertion of two satellites at a different orbits, including ability to deploy satellites at supersynchronous orbit, Lagrangian points, Moon or planetary exploration missions, and a guaranteed upper stage deorbiting or insertion into graveyard orbit.
The new launcher also includes a lengthened fairing up to 20m and a new dual launch system to accommodate larger satellites. Compared to an Ariane 5 ECA model, the payload to GTO increases by 15% to 11.5 tonnes and the cost-per-kilogram of each launch is projected to decline by 20%.
Originally known as the Ariane 5 ECB, Ariane 5 ME was to have its first flight in 2006. However, the failure of the first ECA flight in 2002, combined with a deteriorating satellite industry, caused ESA to cancel development in 2003. Development of the Vinci engine continued, though at a lower pace. The ESA Council of Ministers agreed to fund development of the new upper stage in November 2008. In 2009, EADS Astrium was awarded a €200 million contract, and on April 10, 2012 received another €112 million contract to continue development of the Ariane 5 ME with total development effort expected to cost €1 billion ($1.35 billion).
On 21 November 2012, ESA agreed to continue with the Ariane 5 ME to meet the challenge of lower priced competitors. It was agreed the Vinci upper stage would also be used as the second stage of a new Ariane 6, and further commonality would be sought. Ariane 5 ME qualification flight is scheduled for mid-2018, followed by gradual introduction into service.
Solid propellant stage
Work on the Ariane 5 EAP motors have been continued in the Vega programme. The Vega 1st stage engine—the P80 engine—is a shorter derivation of the EAP. The P80 booster casing is made of filament wound graphite epoxy, much lighter than the current stainless steel casing. A new composite steerable nozzle has been developed while new thermal insulation material and a narrower throat improve the expansion ratio and subsequently the overall performance. Additionally, the nozzle now has electromechanical actuators which have replaced the heavier hydraulic ones used for thrust vector control.
These developments will probably later make their way back into the Ariane programme. The incorporation of the ESC-B with the improvements to the solid motor casing and an uprated Vulcain engine would deliver 27,000 kilograms (60,000 lb) to LEO. This would be developed for any lunar missions but the performance of such a design may not be possible if the higher Max-Q for the launch of this rocket poses a constraint on the mass delivered to orbit.
The finalized design of the next generation rocket, Ariane 6, a smaller rocket capable of launching only a single satellite of 3 to 6.5 tonnes to a geostationary transfer orbit, includes first and second stages, along with two strap-on boosters, using solid propulsion and a liquid hydrogen-fueled cryogenic third stage powered by the same Vinci engine currently under development for the Ariane 5 ME.
While ESA governments are scheduled to decide in December 2014 whether to proceed with full development, the chairman of the German Aerospace Center criticized the current form of the Ariane 6 and the satellite operators are concerned that the rocket will not be fully competitive.
Development is projected to cost €4 billion. Its first test launch is set for 2021. Ariane 6 is planned to be launched for about €70 million ($96 million) per flight or about half of the Ariane 5 rocket's current price.
Ariane 5's first test flight (Ariane 5 Flight 501) on 4 June 1996 failed, with the rocket self-destructing 37 seconds after launch because of a malfunction in the control software. A data conversion from 64-bit floating point value to 16-bit signed integer value to be stored in a variable representing horizontal bias caused a processor trap (operand error) because the floating point value was too large to be represented by a 16-bit signed integer. The software was originally written for the Ariane 4 where efficiency considerations (the computer running the software had an 80% maximum workload requirement) led to four variables being protected with a handler while three others, including the horizontal bias variable, were left unprotected because it was thought that they were "physically limited or that there was a large margin of error". The software, written in Ada, was included in the Ariane 5 through the reuse of an entire Ariane 4 subsystem despite the fact that the particular software containing the bug, which was just a part of the subsystem, was not required by the Ariane 5 because it has a different preparation sequence than the Ariane 4.
The second test flight (L502, on 30 October 1997) was a partial failure. The Vulcain nozzle caused a roll problem, leading to premature shutdown of the core stage. The upper stage operated successfully, but it could not reach the intended orbit.
A subsequent test flight (L503, on 21 October 1998) proved successful and the first commercial launch (L504) occurred on 10 December 1999 with the launch of the XMM-Newton X-ray observatory satellite.
Another partial failure occurred on 12 July 2001, with the delivery of two satellites into an incorrect orbit, at only half the height of the intended GTO. The ESA Artemis telecommunications satellite was able to reach its intended orbit on 31 January 2003, through the use of its experimental ion propulsion system.
The next launch did not occur until 1 March 2002, when the Envisat environmental satellite successfully reached an orbit 800 km above the Earth in the 11th launch. At 8111 kg, it was the heaviest single payload until the launch of the first ATV on March 9, 2008 (19,360 kg).
The first launch of the ECA variant on 11 December 2002 ended in failure when a main booster problem caused the rocket to veer off-course, forcing its self-destruction three minutes into the flight. Its payload of two communications satellites (Stentor and Hot Bird 7), valued at about EUR 630 million, was lost in the ocean. The fault was determined to have been caused by a leak in coolant pipes allowing the nozzle to overheat. After this failure, Arianespace SA delayed the expected January 2003 launch for the Rosetta mission to 26 February 2004, but this was again delayed to early March 2004 due to a minor fault in the foam that protects the cryogenic tanks on the Ariane 5. As of April 2014, the failure of the first ECA launch was the last failure of an Ariane 5; since then, all subsequent launches have been successful, with 59 consecutive successes that stretch back to 9 April 2003 with the launch of INSAT-3A and Galaxy 12 satellites.
On 27 September 2003 the last Ariane 5 G boosted three satellites (including the first European lunar probe, SMART-1), in Flight 162. On 18 July 2004 an Ariane 5 G+ boosted what was at the time the heaviest telecommunication satellite ever, Anik F2, weighing almost 6,000 kg.
The first successful launch of the Ariane 5 ECA took place on 12 February 2005. The payload consisted of the XTAR-EUR military communications satellite, a 'SLOSHSAT' small scientific satellite and a MaqSat B2 payload simulator. The launch had been originally scheduled for October 2004, but additional testing and the military requiring a launch at that time (of an Helios 2A observation satellite) delayed the attempt.
On 11 August 2005, the first Ariane 5GS (featuring the Ariane 5 ECA's improved solid motors) boosted Thaïcom-4/iPStar-1, the heaviest telecommunications satellite to date at 6,505 kg, into orbit.
On 16 November 2005, the third Ariane 5 ECA launch (the second successful ECA launch) took place. It carried a dual payload consisting of Spaceway-F2 for DirecTV and Telkom-2 for PT Telekomunikasi of Indonesia. This was the rocket's heaviest dual payload to date, at more than 8,000 kg.
On 4 May 2007 the Ariane 5 ECA set another new commercial record, lifting into transfer orbit the Astra 1L and Galaxy 17 communication satellites with a combined weight of 8.6 tonnes, and a total payload weight of 9.4 tonnes. This record was again broken by another Ariane 5 ECA, launching the Skynet 5B and Star One C1 satellites, on 11 November 2007. The total payload weight for this launch was 9,535 kg.
On 9 March 2008, the first Ariane 5 ES-ATV was launched to deliver the first ATV called Jules Verne to the International Space Station. The ATV was the heaviest payload ever launched by a European rocket, providing supplies to the space station with necessary propellant, water, air and dry cargo. This was the first operational Ariane mission which involved an engine restart in the upper stage. (The ES-ATV Aestus EPS upper stage was restartable while the ECA HM7-B engine was not.)
On 1 July 2009, an Ariane 5 ECA launched TerreStar-1, the largest commercial telecommunication satellite ever built.
On 28 October 2010, an Ariane 5 ECA launched Eutelsat's W3B (part of its W Series of satellites) and Broadcasting Satellite System Corporation (B-SAT)'s BSAT-3b satellites into orbit. However, the W3B satellite failed to operate shortly after the successful launch and was written off as a total loss due to an oxidizer leak in the satellite's main propulsion system. The BSAT-3b satellite, however, is operating normally.
On 22 April 2011, the Ariane 5 ECA flight VA-201 broke a commercial record, lifting Yahsat 1A and Intelsat New Dawn with a total payload weight of 10,064 kg to transfer orbit. This record was later broken again during the launch of Ariane 5 ECA flight VA-208 on 2 August 2012, lifting a total of 10,182 kg into the planned geosynchronous transfer orbit.
Ariane 5 flights
& Time (UTC)
|Flight (Vol)||Configuration||Serial number||Payload||Result||#|
|1997-10-30 13:43:00||V-101||5G||502||MaqSat-H, TEAMSAT, MaqSat-B, YES||Partial failure||2|
|1998-10-21 16:37:21||V-112||5G||503||MaqSat 3, ARD||Success||3|
|2000-03-21 23:28:19||V-128||5G||505||INSAT-3B, AsiaStar||Success||5|
|2000-09-14 22:54:07||V-130||5G||506||Astra 2B, GE-7||Success||6|
|2000-11-16 01:07:07||V-135||5G||507||PAS-1R, Amsat P3D, STRV 1C, STRV 1D||Success||7|
|2000-12-20 00:26:00||V-138||5G||508||Astra 2D, GE-8, LDREX||Success||8|
|2001-03-08 22:51:00||V-140||5G||509||Eutelsat 28A, BSAT-2a||Success||9|
|2001-07-12 22:58:00||V-142||5G||510||Artemis, BSAT-2b||Partial failure||10|
|2002-07-05 23:22:00||V-153||5G||512||Stellat 5, N-Star c||Success||12|
|2002-08-28 22:45:00||V-155||5G||513||Atlantic Bird 1, Meteosat 8||Success||13|
|2002-12-11 22:22:00||V-157||5ECA||517||Hot Bird 7, Stentor||Failure||14|
|2003-04-09 22:52:19||V-160||5G||514||INSAT-3A, Galaxy 12||Success||15|
|2003-06-11 22:38:15||V-161||5G||515||Optus and Defence C1, BSAT-2c||Success||16|
|2003-09-27 23:14:46||V-162||5G||516||INSAT-3E, eBird 1, SMART-1||Success||17|
|2004-07-18 00:44:00||V-163||5G+||519||Anik F2||Success||19|
|2004-12-18 16:26:00||V-165||5G+||520||Helios 2A, Essaim 1, 2, 3, 4, PARASOL, Nanosat 01||Success||20|
|2005-02-12 21:03:00||V-164||5ECA||521||XTAR-EUR, Maqsat-B2, Sloshsat||Success||21|
|2005-08-11 08:20:00||V-166||5GS||523||Thaicom 4||Success||22|
|2005-10-13 22:32:00||V-168||5GS||524||Syracuse 3A, Galaxy 15||Success||23|
|2005-11-16 23:46:00||V-167||5ECA||522||Spaceway F2, TELKOM-2||Success||24|
|2005-12-21 22:33:00||V-169||5GS||525||INSAT-4A, Meteosat 9||Success||25|
|2006-03-11 22:32:50||V-170||5ECA||527||Spainsat, Hot Bird 7A||Success||26|
|2006-05-26 21:09||V-171||5ECA||529||Satmex 6, Thaicom 5||Success||27|
|2006-08-11 22:15||V-172||5ECA||531||JCSAT-10, Syracuse 3B||Success||28|
|2006-10-13 20:56:00||V-173||5ECA||533||DirecTV-9S, Optus D1, LDREX-2||Success||29|
|2006-12-08 22:08:00||V-174||5ECA||534||WildBlue 1, AMC-18||Success||30|
|2007-03-11 22:03||V-175||5ECA||535||Skynet 5A, INSAT-4B||Success||31|
|2007-05-04 22:29||V-176||5ECA||536||Astra 1L, Galaxy 17||Success||32|
|2007-08-14 23:44||V-177||5ECA||537||Spaceway-3, BSAT-3A||Success||33|
|2007-10-05 22:02||V-178||5GS||526||Intelsat 11, Optus D2||Success||34|
|2007-11-14 22:06||V-179||5ECA||538||Skynet 5B, Star One C1||Success||35|
|2007-12-21 21:41||V-180||5GS||530||RASCOM-QAF 1, Horizons-2||Success||36|
|2008-03-09 04:03||V-181||5ES||528||ATV-1 "Jules Verne"||Success||37|
|2008-04-18 22:17||V-182||5ECA||539||Star One C2, Vinasat-1||Success||38|
|2008-06-12 22:05||V-183||5ECA||540||Turksat 3A, Skynet 5C||Success||39|
|2008-07-07 21:47||V-184||5ECA||541||Badr-6, ProtoStar I||Success||40|
|2008-08-14 20:44||V-185||5ECA||542||AMC-21, Superbird 7||Success||41|
|2008-12-20 22:35||V-186||5ECA||543||Eutelsat W2M, Hot Bird 9||Success||42|
|2009-02-12 22:09||V-187||5ECA||545||Hot Bird 10, NSS-9, Spirale A, Spirale B||Success||43|
|2009-05-14 13:12||V-188||5ECA||546||Herschel, Planck||Success||44|
|2009-08-21 22:09||V-190||5ECA||548||JCSAT-12, Optus D3||Success||46|
|2009-10-01 21:59||V-191||5ECA||549||Amazonas 2, COMSATBw-1||Success||47|
|2009-10-29 20:00||V-192||5ECA||550||NSS-12, Thor 6||Success||48|
|2009-12-18 16:26||V-193||5GS||532||Helios 2B||Success||49|
|2010-05-21 22:01||V-194||5ECA||551||Astra 3B, COMSATBw-2||Success||50|
|2010-06-26 21:41||V-195||5ECA||552||Arabsat-5A, COMS-1||Success||51|
|2010-08-04 20:59||V-196||5ECA||554||Nilesat 201, RASCOM-QAF 1R||Success||52|
|2010-10-28 21:51||V-197||5ECA||555||Eutelsat W3B, BSAT-3b||Success||53|
|2010-11-26 18:39||V-198||5ECA||556||Intelsat 17, HYLAS 1||Success||54|
|2010-12-29 21:27||V-199||5ECA||557||Koreasat 6, HispaSat-1E||Success||55|
|2011-02-16 21:50||V-200||5ES||544||ATV-2 "Johannes Kepler"||Success||56|
|2011-04-22 21:37||VA-201||5ECA||558||Yahsat 1A, Intelsat New Dawn||Success||57|
|2011-05-20 20:38||VA-202||5ECA||559||ST-2, GSAT-8||Success||58|
|2011-08-06 22:52||VA-203||5ECA||560||Astra 1N, BSAT 3c||Success||59|
|2011-09-21 21:38||VA-204||5ECA||561||Arabsat 5C, SES-2||Success||60|
|2012-03-23 04:34||VA-205||5ES||553||ATV-3 "Edoardo Amaldi"||Success||61|
|2012-05-15 22:13||VA-206||5ECA||562||JCSAT-13, Vinasat-2||Success||62|
|2012-07-05 21:36||VA-207||5ECA||563||EchoStar XVII, MSG-3||Success||63|
|2012-08-02 20:54||VA-208||5ECA||564||INTELSAT 20, HYLAS 2||Success||64|
|2012-09-28 21:18||VA-209||5ECA||565||Astra 2F, GSAT-10||Success||65|
|2012-11-10 21:05||VA-210||5ECA||566||Eutelsat 21B, Star One C3||Success||66|
|2012-12-19 21:49||VA-211||5ECA||567||Skynet 5D, MEXSAT-3||Success||67|
|2013-02-07 21:36||VA-212||5ECA||568||Amazonas-3, Azerspace-1/Africasat-1a||Success||68|
|2013-06-05 21:52||VA-213||5ES||592||ATV-4 "Albert Einstein"||Success||69|
|2013-07-25 19:54||VA-214||5ECA||569||Alphasat I-XL, INSAT-3D||Success||70|
|2013-08-29 20:30||VA-215||5ECA||570||Eutelsat 25B / Es'hail 1, GSAT-7||Success||71|
|2014-02-06 21:30||VA-217||5ECA||572||ABS-2, Athena-Fidus||Success||72|
|2014-03-22 22:04||VA-216||5ECA||571||Astra 5B, Amazonas 4A||Success||73|
|2014-07-29 23:47||VA-219||5ES||593||ATV-5 "Georges Lemaître"||Success||74|
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- Comparison of orbital launch systems
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