Ariane 5

Ariane 5
	Ariane 5 flight VA-256 on the launch pad with the James Webb Space Telescope in December 2021.
Function	Heavy launch vehicle
Manufacturer	ArianeGroup; for ESA
Country of origin	20 ESA member states: Austria ; Belgium ; Czech Republic ; Denmark ; Finland ; France ; Germany ; Greece ; Ireland ; Italy ; Luxembourg ; Netherlands ; Norway ; Poland ; Portugal ; Romania ; Spain ; Sweden ; Switzerland ; United Kingdom ;
Cost per launch	€139–185 million [1]
Size
Height	46–52 m (151–171 ft)
Diameter	5.4 m (18 ft)
Mass	777,000 kg (1,713,000 lb)
Stages	2
Capacity
Payload to Low Earth orbit
Altitude	260 km (160 mi) (circular)
Orbital inclination	51.6°
Mass	G: 16,000 kg (35,000 lb); ES: over 20,000 kg (44,000 lb)[2]
Payload to GTO
Mass	G: 6,950 kg (15,320 lb); G+: 6,950 kg (15,320 lb); GS: 6,100 kg (13,400 lb); ECA: 10,865 kg (23,953 lb)[3];
Associated rockets
Family	Ariane
Comparable	Atlas V 551; Delta IV Heavy; Falcon 9 Block 5; H-IIB; Long March 5; Proton-M; GSLV Mark III;
Launch history
Status	G: Retired; G+: Retired; GS: Retired; ECA: Active; ES: Retired;
Launch sites	Centre Spatial Guyanais, ELA-3
Total launches	114 G: 16; G+: 3; GS: 6; ECA: 81; ES: 8;
Success(es)	109 G: 13; G+: 3; GS: 6; ECA: 79; ES: 8;
Failure(s)	2 (G: 1, ECA: 1)
Partial failure(s)	3 (G: 2, ECA: 1)
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; ECA: 7 September 2022; ES: 25 July 2018;
People or cargo transported	XMM-Newton; Envisat; Rosetta; ATV; Herschel; Planck; Galileo; Webb;
Boosters (G, G+) – EAP P238
No. boosters	2
Height	31.6 m (104 ft)
Diameter	3.06 m (10.0 ft)
Gross mass	270 t (270 long tons; 300 short tons)
Powered by	P238
Maximum thrust	6,650 kN (1,490,000 lbf)
Total thrust	13,300 kN (3,000,000 lbf)
Burn time	130 seconds
Propellant	AP, Aluminium, HTPB
Boosters (GS, ECA, ES) – EAP P241
No. boosters	2
Height	31.6 m (104 ft)
Diameter	3.06 m (10.0 ft)
Empty mass	33 t (32 long tons; 36 short tons)
Gross mass	273 t (269 long tons; 301 short tons)
Powered by	P241
Maximum thrust	7,080 kN (1,590,000 lbf)
Total thrust	14,160 kN (3,180,000 lbf)
Burn time	140 seconds
Propellant	AP, Aluminium, HTPB
Core stage (G, G+, GS) – EPC H158
Height	23.8 m (78 ft)
Diameter	5.4 m (18 ft)
Empty mass	12,200 kg (26,900 lb)
Gross mass	170,500 kg (375,900 lb)
Powered by	G, G+: Vulcain 1; GS: Vulcain 1B
Maximum thrust	1,015 kN (228,000 lbf) (vacuum)
Specific impulse	440 seconds (vacuum)
Burn time	605 seconds
Propellant	LH2 / LOX
Core stage (ECA, ES) – EPC H173
Height	23.8 m (78 ft)
Diameter	5.4 m (18 ft)
Empty mass	14,700 kg (32,400 lb)
Gross mass	184,700 kg (407,200 lb)
Powered by	Vulcain 2
Maximum thrust	960 kN (220,000 lbf); (sea level); 1,390 kN (310,000 lbf) (vacuum)
Specific impulse	310 seconds (sea level); 432 seconds (vacuum)
Burn time	540 seconds
Propellant	LH2 / LOX
Second stage (G) – EPS L9.7
Height	3.4 m (11 ft)
Diameter	5.4 m (18 ft)
Empty mass	1,200 kg (2,600 lb)
Gross mass	10,900 kg (24,000 lb)
Powered by	Aestus
Maximum thrust	27 kN (6,100 lbf)
Burn time	1100 seconds
Propellant	MMH / N2O4
Second stage (G+, GS, ES) – EPS L10
Height	3.4 m (11 ft)
Diameter	5.4 m (18 ft)
Empty mass	1,200 kg (2,600 lb)
Gross mass	11,200 kg (24,700 lb)
Powered by	Aestus
Maximum thrust	27 kN (6,100 lbf)
Burn time	1170 seconds
Propellant	MMH / N2O4
Second stage (ECA) – ESC-A
Height	4.711 m (15.46 ft)
Diameter	5.4 m (18 ft)
Empty mass	4,540 kg (10,010 lb)
Gross mass	19,440 kg (42,860 lb)
Powered by	HM7B
Maximum thrust	67 kN (15,000 lbf)
Specific impulse	446 seconds
Burn time	945 seconds
Propellant	LH2 / LOX

Ariane 5 is a European heavy-lift space launch vehicle developed and operated by Arianespace for the European Space Agency (ESA). It is launched from the Centre Spatial Guyanais (CSG) in French Guiana. It has been used to deliver payloads into geostationary transfer orbit (GTO) or low Earth orbit (LEO). The launch vehicle had a streak of 82 consecutive successful launches between 9 April 2003 and 12 December 2017. Since 2014,[4] Ariane 6, a direct successor system, is in development.[5]

The system was designed as an expendable launch system by the Centre national d'études spatiales (CNES), the French government's space agency, in cooperation with various European partners. Despite not being a direct derivative of its predecessor launch vehicle program, it is classified as part of the Ariane rocket family. ArianeGroup is the prime contractor for the manufacturing of the vehicles, leading a multi-country consortium of other European contractors. Ariane 5 was originally intended to launch the Hermes spacecraft, and thus it is rated for human space launches.

Since its first launch, Ariane 5 has been refined in successive versions: "G", "G+", "GS", "ECA", and most recently, "ES". The system has a commonly used dual-launch capability, where up to two large geostationary belt communication satellites can be mounted using a SYLDA (Système de Lancement Double Ariane, meaning "Ariane Double-Launch System") carrier system. Up to three, somewhat smaller, main satellites are possible depending on size using a SPELTRA (Structure Porteuse Externe Lancement Triple Ariane, which translates to "Ariane Triple-Launch External Carrier Structure"). Up to eight secondary payloads, usually small experiment packages or minisatellites, can be carried with an ASAP (Ariane Structure for Auxiliary Payloads) platform.

Following the launch of 15 August 2020, Arianespace signed the contracts for the last eight Ariane 5 launches, before it is succeeded by the new Ariane 6 launcher, according to Daniel Neuenschwander, director of space transportation at the ESA.[6][5]

Vehicle description

Cryogenic main stage

Vulcain engine

Ariane 5's cryogenic H173 main stage (H158 for Ariane 5G, G+, and GS) is called the EPC (Étage Principal Cryotechnique — Cryotechnic Main Stage). It consists of a 5.4 m (18 ft) diameter by 30.5 m (100 ft) high tank with two compartments, one for liquid oxygen and one for liquid hydrogen, and a Vulcain 2 engine at the base with a vacuum thrust of 1,390 kN (310,000 lb_f). The H173 EPC weighs about 189 t (417,000 lb), including 175 t (386,000 lb) of propellant.[7] After the main cryogenic stage runs out of fuel, it re-enters the atmosphere for an ocean splashdown.

Solid boosters

Attached to the sides are two P241 (P238 for Ariane 5G and G+) solid rocket boosters (SRBs or EAPs from the French Étages d'Accélération à Poudre), each weighing about 277 t (611,000 lb) full and delivering a thrust of about 7,080 kN (1,590,000 lb_f). They are fueled by a mix of ammonium perchlorate (68%) and aluminium fuel (18%) and HTPB (14%). They each burn for 130 seconds before being dropped into the ocean. The 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 has occasionally been 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 in 2009. One of the two boosters was successfully recovered and returned to the Guiana Space Center for analysis.[8] Prior to that mission, the last such recovery and testing was done in 2003.

The French M51 submarine-launched ballistic missile (SLBM) shares a substantial amount of technology with these boosters.

In February 2000, the suspected nose cone of an Ariane 5 booster washed ashore on the South Texas coast, and was recovered by beachcombers before the government could get to it.[9]

Second stage

EPS Upper Stage used on Ariane 5ES

The second stage is on top of the main stage and below the payload. The original Ariane — Ariane 5G — used the EPS (Étage à Propergols Stockables — Storable Propellant Stage), which was fueled by monomethylhydrazine (MMH) and nitrogen tetroxide, containing 10,000 kg (22,000 lb) of storable propellant. The EPS was subsequently improved for use on the Ariane 5G+, GS, and ES.

The EPS upper stage is capable of repeated ignition, first demonstrated 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 (ATV) into a circular parking orbit, followed by a third burn after ATV deployment to de-orbit the stage. This procedure was repeated for all subsequent ATV flights.

Ariane 5ECA uses the ESC (Étage Supérieur Cryotechnique — Cryogenic Upper Stage), which is fueled by liquid hydrogen and liquid oxygen. The ESC uses the HM7B engine previously used in the Ariane 4 third stage. The propellent load of 14.7 tonne allows the engine to burn for 945 seconds while providing 6.5 tonne of thrust. The ESC provides roll control during powered flight and full attitude control during payload separation using hydrogen gas thrusters. Oxygen gas thrusters allow longitudinal acceleration after engine cutoff. The flight assembly includes the Vehicle Equipment Bay, with flight electronics for the entire rocket, and the payload interface and structural support.[10][11]

Fairing

The payload and all upper stages are covered at launch by a fairing for aerodynamic stability and protection from heating during supersonic flight and acoustic loads. It is jettisoned once sufficient altitude has been reached, typically above 100 km (62 mi). It is made by Ruag Space and since flight VA-238 it is composed of 4 panels.[12]

Variants

Variant	Description
G	The original version is dubbed Ariane 5G (Generic) and had a launch mass of 737 t (1,625,000 lb). Its payload capability to geostationary transfer orbit (GTO) was 6,900 kg (15,200 lb) for a single satellite or 6,100 kg (13,400 lb) for dual launches. It flew 17 times with one failure and two partial failures.[13]
G+	The Ariane 5G+ had an improved EPS second stage, with a GTO capacity of 7,100 kg (15,700 lb) for a single payload or 6,300 kg (13,900 lb) for two. It flew three times in 2004, with no failures.[14]
GS	At the time of the failure of the first Ariane 5ECA flight in 2002, all Ariane 5 launchers in production were ECA versions. Some of the ECA cores were modified to use the original Vulcain engine and tank volumes while the failure was investigated; these vehicles were designated Ariane 5GS. The GS used the improved EAP boosters of the ECA variant and the improved EPS of the G+ variant, but the increased mass of the modified ECA core compared to the G and G+ core resulted in slightly reduced payload capacity.[15] Ariane 5GS could carry a single payload of 6,600 kg (14,600 lb) or a dual payload of 5,800 kg (12,800 lb) to GTO. The Ariane 5GS flew 6 times from 2005 to 2009 with no failures.[16]
ECA	The Ariane 5ECA (Evolution Cryotechnique type A), first successfully flown in 2005, uses an improved Vulcain 2 first-stage engine with a longer, more efficient nozzle with a more efficient flow cycle and denser propellant ratio. The new ratio required length modifications to the first-stage tanks. The EPS second stage was replaced by the ESC-A (Etage Supérieur Cryogénique-A), which has a dry weight of 4,540 kg (10,010 lb) and is powered by an HM-7B engine burning 14,900 kg (32,800 lb) of cryogenic propellant. The ESC-A uses the liquid oxygen tank and lower structure from the Ariane 4's H10 third stage, mated to a new liquid hydrogen tank. Additionally, the EAP booster casings were lightened with new welds and carry more propellant. The Ariane 5ECA started with a GTO launch capacity of 9,100 kg (20,100 lb) for dual payloads or 9,600 kg (21,200 lb) for a single payload.[17] Later batches: PB+ and PC, increased the max payload to GTO to 11,115 kg (24,504 lb).[3]
ES	The Ariane 5ES (Evolution Storable) has an estimated LEO launch capacity of 21,000 kg (46,000 lb). It includes all the performance improvements of Ariane 5ECA core and boosters but replaces the ESC-A second stage with the restartable EPS used on Ariane 5GS variants. It was used to launch the Automated Transfer Vehicle (ATV) into a 260 km (160 mi) circular low Earth orbit inclined at 51.6° and has been used 3 times to launch 4 Galileo navigation satellites at a time directly into their operational orbit.[2] The Ariane 5ES flew 8 times from 2008 to 2018 with no failures.
ME	The Ariane 5ME (Mid-life Evolution) was under development until the end of 2014. The last ESA ministerial council of December 2014 has cut further funding for Ariane 5ME in favour of developing Ariane 6. Last activities for Ariane 5ME were completed at the end of 2015. Activities on development of the VINCI upper stage were transferred to Ariane 6.

Launch system status: Retired · Cancelled · Operational · Under development

Launch pricing and market competition

As of November 2014, the Ariane 5 commercial launch price for launching a "midsize satellite in the lower position" was approximately €50 million,[18] competing for commercial launches in an increasingly competitive market.

The heavier satellite is launched in the upper position on a typical dual-satellite Ariane 5 launch and is priced higher than the lower satellite,[19] on the order of €90 million as of 2013.[20][21]

Total launch price of an Ariane 5 – which can transport up to two satellites to space, one in the "upper" and one in the "lower" positions – was around €150 million as of January 2015.[21]

Cancelled plans for future developments

Belgian components produced for the Ariane 5 European heavy-lift launch vehicle explained

Ariane 5 ME

The Ariane 5 ME (Mid-life Evolution) was in development into early 2015, and was seen as a stopgap between Ariane 5ECA/Ariane 5ES and the new Ariane 6. With first flight planned for 2018, it would have become ESA's principal launcher until the arrival of the new Ariane 6 version. ESA halted funding for the development of Ariane 5ME in late 2014 to prioritize development of Ariane 6.[22]

The Ariane 5ME was to use a new upper stage, with increased propellant volume, powered by the new Vinci engine. Unlike the HM-7B engine, it was to be able to restart several times, allowing for complex orbital maneuvers such as insertion of two satellites into different orbits, direct insertion into geosynchronous orbit, planetary exploration missions, and guaranteed upper stage deorbiting or insertion into graveyard orbit.[23][24] The launcher was also to include a lengthened fairing up to 20 m (66 ft) and a new dual launch system to accommodate larger satellites. Compared to an Ariane 5ECA model, the payload to GTO was to increase by 15% to 11,500 kg (25,400 lb) and the cost-per-kilogram of each launch is projected to decline by 20%.[23]

Development

Originally known as the Ariane 5ECB, Ariane 5ME 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.[25] 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.[26]

In 2009, EADS Astrium was awarded a €200 million contract,[27] and on 10 April 2012 received another €112 million contract to continue development of the Ariane 5ME [28] with total development effort expected to cost €1 billion.[29]

On 21 November 2012, ESA agreed to continue with the Ariane 5ME 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.[24] Ariane 5ME qualification flight was scheduled for mid-2018, followed by gradual introduction into service.[23]

On 2 December 2014, ESA decided to stop funding the development of Ariane 5ME and instead focus on Ariane 6, which was expected to have a lower cost per launch and allow more flexibility in the payloads (using two or four P120C solid boosters depending on total payload mass).[22]

Solid propellant stage

Work on the Ariane 5 EAP motors has been continued in the Vega programme. The Vega 1st stage engine – the P80 engine – is a shorter derivation of the EAP.[30] 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.[24][31] The incorporation of the ESC-B with the improvements to the solid motor casing and an uprated Vulcain engine would deliver 27,000 kg (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 launch vehicle poses a constraint on the mass delivered to orbit.[32]

Ariane 6

The design brief of the next generation launch vehicle Ariane 6 called for a lower-cost and smaller launch vehicle capable of launching a single satellite of up to 6,500 kg (14,300 lb) to GTO.[33] However, after several permutations the finalized design was nearly identical in performance to the Ariane 5,[34] focusing instead on lowering fabrication costs and launch prices. As of March 2014, Ariane 6 was projected to be launched for about €70 million per flight, about half of the Ariane 5 price.[33]

Initially development of Ariane 6 was projected to cost €3.6 billion.[35] In 2017, the ESA set 16 July 2020 as the deadline for the first flight.[36] As of June 2022, Arianespace expects the maiden flight to occur in 2023.[37]

Notable launches

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.[38] 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)[39] because the floating-point value was too large to be represented by a 16-bit signed integer. The software had been written for the Ariane 4 where efficiency considerations (the computer running the software had an 80% maximum workload requirement[39]) 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 safety".[39] 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.[39]

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 of 800 km (500 mi) above the Earth in the 11th launch. At 8,111 kg (17,882 lb), it was the heaviest single payload until the launch of the first ATV on 9 March 2008, at 19,360 kg (42,680 lb).

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 €630 million, was lost in the Atlantic 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 June 2017, the failure of the first ECA launch was the last failure of an Ariane 5; since then, 82 consecutive launches have been successful, from April 2003 with the launch of INSAT-3A and Galaxy 12 satellites,[40] to flight 240 in December 2017.

On 27 September 2003, the last Ariane 5G boosted three satellites (including the first European lunar probe, SMART-1), in Flight 162. On 18 July 2004, an Ariane 5G+ boosted what was at the time the heaviest telecommunication satellite ever, Anik F2, weighing almost 6,000 kg (13,000 lb).

The first successful launch of the Ariane 5ECA 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 scheduled for October 2004, but additional testing and a military launch (of a Helios 2A observation satellite) delayed the attempt.

On 11 August 2005, the first Ariane 5GS (featuring the Ariane 5ECA's improved solid motors) boosted Thaicom 4, the heaviest telecommunications satellite to date at 6,505 kg (14,341 lb),[41] into orbit.

On 16 November 2005, the third Ariane 5ECA 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 launch vehicle's heaviest dual payload to date, at more than 8,000 kg (18,000 lb).

On 27 May 2006, an Ariane 5ECA launch vehicle set a new commercial payload lifting record of 8,200 kg (18,100 lb). The dual-payload consisted of the Thaicom 5 and Satmex 6 satellites.[42]

On 4 May 2007, the Ariane 5ECA set another new commercial record, lifting into transfer orbit the Astra 1L and Galaxy 17 communication satellites with a combined weight of 8,600 kg (19,000 lb), and a total payload weight of 9,400 kg (20,700 lb).[43] This record was again broken by another Ariane 5ECA, launching the Skynet 5B and Star One C1 satellites, on 11 November 2007. The total payload weight for this launch was of 9,535 kg (21,021 lb).[44]

On 9 March 2008, the first Ariane 5ES-ATV was launched to deliver the first ATV called Jules Verne to the International Space Station (ISS). The ATV was the heaviest payload ever launched by a European launch vehicle, 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 5ECA launched TerreStar-1 (now EchoStar T1), which was then, at 6,910 kg (15,230 lb), the largest and most massive commercial telecommunication satellite ever built at that time[45] until being overtaken by Telstar 19 Vantage, at 7,080 kg (15,610 lb), launched aboard Falcon 9. The satellite was launched into a lower-energy orbit than a usual GTO, with its initial apogee at roughly 17,900 km (11,100 mi).[46]

On 28 October 2010, an Ariane 5ECA launched Eutelsat's W3B (part of its W Series of satellites) and Broadcasting Satellite System Corporation (B-SAT)'s BSAT-3b satellites into orbit. But 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.[47] The BSAT-3b satellite, however, is operating normally.[48]

The VA253 launch on 15 August 2020 introduced two small changes that increased lift capacity by about 85 kg (187 lb); these were a lighter avionics and guidance-equipment bay, and modified pressure vents on the payload fairing, which were required for the subsequent launch of the James Webb Space Telescope. It also debuted a location system using Galileo navigation satellites.[49]

On 25 December 2021, VA256 launched the James Webb Space Telescope towards a Sun–Earth L₂ halo orbit.[50] The precision of trajectory following launch led to fuel savings credited with potentially doubling the lifetime of the telescope by leaving more hydrazine propellant on-board for station-keeping than was expected.[50][51] According to Rudiger Albat, the program manager for Ariane 5, efforts had been made to select components for this flight that had performed especially well during pre-flight testing, including "one of the best Vulcain engines that we've ever built."[51]

GTO payload weight records

On 22 April 2011, the Ariane 5ECA flight VA-201 broke a commercial record, lifting Yahsat 1A and Intelsat New Dawn with a total payload weight of 10,064 kg (22,187 lb) to transfer orbit.[52] This record was later broken again during the launch of Ariane 5ECA flight VA-208 on 2 August 2012, lifting a total of 10,182 kg (22,447 lb) into the planned geosynchronous transfer orbit,[53] which was broken again 6 months later on flight VA-212 with 10,317 kg (22,745 lb) sent towards geosynchronous transfer orbit.[54] In June 2016, the GTO record was raised to 10,730 kg (23,660 lb),[55] on the first rocket in history that carried a satellite dedicated to financial institutions.[56] The payload record was pushed a further 5 kg (11 lb), up to 10,735 kg (23,667 lb) on 24 August 2016 with the launch of Intelsat 33e and Intelsat 36.[57] On 1 June 2017, the payload record was broken again to 10,865 kg (23,953 lb) carrying ViaSat-2 and Eutelsat-172B.[58] In 2021 VA-255 put 11,210 kg into GTO.

VA241 anomaly

On 25 January 2018, an Ariane 5ECA launched SES-14 and Al Yah 3 satellites. About 9 minutes and 28 seconds after launch, a telemetry loss occurred between the launch vehicle and the ground controllers. It was later confirmed, about 1 hour and 20 minutes after launch, that both satellites were successfully separated from the upper stage and were in contact with their respective ground controllers,[59] but that their orbital inclinations were incorrect as the guidance systems might have been compromised. Therefore, both satellites conducted orbital procedures, extending commissioning time.[60] SES-14 needed about 8 weeks longer than planned commissioning time, meaning that entry into service was reported early September instead of July.[61] Nevertheless, SES-14 is still expected to be able to meet the designed lifetime. This satellite was originally to be launched with more propellant reserve on a Falcon 9 launch vehicle since the Falcon 9, in this specific case, was intended to deploy this satellite into a high inclination orbit that would require more work from the satellite to reach its final geostationary orbit.[62] The Al Yah 3 was also confirmed healthy after more than 12 hours without further statement, and like SES-14, Al Yah 3's maneuvering plan was also revised to still fulfill the original mission.[63] As of 16 February 2018, Al Yah 3 was approaching the intended geostationary orbit, after series of recovery maneuvers had been performed.[64] The investigation showed that invalid inertial units' azimuth value had sent the vehicle 17° off course but to the intended altitude, they had been programmed for the standard geostationary transfer orbit of 90° when the payloads were intended to be 70° for this supersynchronous transfer orbit mission, 20° off norme.[65] This mission anomaly marked the end of 82nd consecutive success streak since 2003.[66]

Launch history

Launch statistics

Ariane 5 launch vehicles have accumulated 114 launches since 1996, 109 of which were successful, yielding a 95.6% success rate. Between April 2003 and December 2017, Ariane 5 flew 83 consecutive missions without failure, but the launch vehicle suffered a partial failure in January 2018.[67]

Rocket configurations

1

2

3

4

5

6

7

1996

2000

2004

2008

2012

2016

2020

G
G+
GS
ES
ECA

Launch outcomes

1

2

3

4

5

6

7