Model: Ariane 5.

Ariane 5 Credit - © Mark Wade

Orbital launch vehicle. Other Family: Active. Country: France. Status: Active.

The Ariane 5 was a completely new design, unrelated to the earlier Ariane 1 to 4. It consisted of a single-engine Lox/LH2 core stage flanked by two solid rocket boosters. Preparatory work began in 1984. Full scale development began in 1988 and cost $ 8 billion. The design was sized for the Hermes manned spaceplane, later cancelled. This resulted in the booster being a bit too large for the main commercial payload, geosynchronous communications satellites. As a result, development of an uprated version capable of launching two such satellites at a time was funded in 2000.

Manufacturer: EADS. Launches: 36. Failures: 2. Success Rate: 94.44%. First Launch Date: 1996-06-04. Last Launch Date: 2007-12-21. Launch data is: continuing.

Model: Ariane 5G.

Ariane 5G

Status: Active.

Initial version of the Ariane 5, a bit too large for the main commercial geosynchronous communications satellite payloads.

Launches: 16. Failures: 1. First Launch Date: 1996-06-04. Last Launch Date: 2003-09-27. LEO Payload: 16,000 kg (35,000 lb). to: 407 km Orbit. at: 51.60 degrees. Payload: 6,800 kg (14,900 lb). to a: Geosynchronous transfer, 7 deg inclination trajectory. Apogee: 40,000 km (24,000 mi). Associated Spacecraft: ARD, Artemis, AS 2100, Cluster, Envisat, Eurostar 2000, FS-1300, HS 376, HS 702, Insat 3, Italsat, LDREX, MAQSAT, MSG, Oscar, Rosetta, Spacebus 3000, Star bus, STRV, XMM, YES, Hermes, ESA Automated Transfer Vehicle, ESA MTFF-Derived Space Station. Other Associated Spacecraft: ESA Polar Platform, ESA ACRV. Liftoff Thrust: 11,400.000 kN (2,562,800 lbf). Total Mass: 746,000 kg (1,644,000 lb). Core Diameter: 5.40 m (17.70 ft). Total Length: 54.05 m (177.32 ft). Launch Price $: 180.000 million. in: 2000 price dollars.

• Stage0: 2 x Ariane 5-0. Gross Mass: 277,500 kg (611,700 lb). Empty Mass: 39,800 kg (87,700 lb). Motor: 1 x P230. Thrust (vac): 6,470.000 kN (1,454,510 lbf). Isp: 275 sec. Burn time: 129 sec. Length: 31.60 m (103.60 ft). Diameter: 3.05 m (10.00 ft). Propellants: Solid.

• Stage1: 1 x Ariane H155. Gross Mass: 170,800 kg (376,500 lb). Empty Mass: 12,700 kg (27,900 lb). Motor: 1 x Vulcain. Thrust (vac): 1,114.000 kN (250,437 lbf). Isp: 430 sec. Burn time: 589 sec. Length: 30.50 m (100.00 ft). Diameter: 5.46 m (17.91 ft). Propellants: Lox/LH2.

• Stage2: 1 x Ariane 5-2. Gross Mass: 12,500 kg (27,500 lb). Empty Mass: 2,700 kg (5,900 lb). Motor: 1 x Aestus. Thrust (vac): 27.400 kN (6,160 lbf). Isp: 324 sec. Burn time: 1,100 sec. Length: 3.36 m (11.02 ft). Diameter: 3.96 m (12.99 ft). Propellants: N2O4/MMH.

Launches: 12. Failures: 1. First Launch Date: 2002-12-11. Last Launch Date: 2007-11-14. LEO Payload: 16,000 kg (35,000 lb). to: 407 km Orbit. at: 51.60 degrees. Payload: 10,500 kg (23,100 lb). to a: Geosynchronous transfer, 7 deg inclination trajectory. Associated Spacecraft: Eurostar 2000, Spacebus 3000. Liftoff Thrust: 15,360.000 kN (3,453,060 lbf). Total Mass: 777,000 kg (1,712,000 lb). Core Diameter: 5.40 m (17.70 ft). Total Length: 59.00 m (193.00 ft).

• Stage0: 2 x Ariane 5 EAP. Gross Mass: 278,330 kg (613,610 lb). Empty Mass: 38,200 kg (84,200 lb). Motor: 1 x P241. Thrust (vac): 6,470.000 kN (1,454,510 lbf). Isp: 275 sec. Burn time: 130 sec. Length: 31.60 m (103.60 ft). Diameter: 3.05 m (10.00 ft). Propellants: Solid.

• Stage1: 1 x Ariane 5 EPC. Gross Mass: 186,000 kg (410,000 lb). Empty Mass: 12,700 kg (27,900 lb). Motor: 1 x Vulcain 2. Thrust (vac): 1,114.000 kN (250,437 lbf). Isp: 434 sec. Burn time: 650 sec. Length: 30.50 m (100.00 ft). Diameter: 5.46 m (17.91 ft). Propellants: Lox/LH2.

• Stage2: 1 x Ariane 5 ESC A. Gross Mass: 16,500 kg (36,300 lb). Empty Mass: 2,100 kg (4,600 lb). Motor: 1 x HM7-B. Thrust (vac): 64.700 kN (14,545 lbf). Isp: 446 sec. Burn time: 960 sec. Length: 9.00 m (29.50 ft). Diameter: 5.46 m (17.91 ft). Propellants: Lox/LH2.

• Stage0: 2 x Ariane 5 EAP. Gross Mass: 278,330 kg (613,610 lb). Empty Mass: 38,200 kg (84,200 lb). Motor: 1 x P241. Thrust (vac): 6,470.000 kN (1,454,510 lbf). Isp: 275 sec. Burn time: 130 sec. Length: 31.60 m (103.60 ft). Diameter: 3.05 m (10.00 ft). Propellants: Solid.

• Stage1: 1 x Ariane 5 EPC. Gross Mass: 186,000 kg (410,000 lb). Empty Mass: 12,700 kg (27,900 lb). Motor: 1 x Vulcain 2. Thrust (vac): 1,114.000 kN (250,437 lbf). Isp: 434 sec. Burn time: 650 sec. Length: 30.50 m (100.00 ft). Diameter: 5.46 m (17.91 ft). Propellants: Lox/LH2.

• Stage2: 1 x Ariane 5 EPS L10. Gross Mass: 12,750 kg (28,100 lb). Empty Mass: 2,750 kg (6,060 lb). Motor: 1 x Aestus. Thrust (vac): 27.400 kN (6,160 lbf). Isp: 324 sec. Burn time: 1,100 sec. Length: 3.36 m (11.02 ft). Diameter: 3.96 m (12.99 ft). Propellants: N2O4/MMH.

• Stage0: 2 x Ariane 5-0. Gross Mass: 277,500 kg (611,700 lb). Empty Mass: 39,800 kg (87,700 lb). Motor: 1 x P230. Thrust (vac): 6,470.000 kN (1,454,510 lbf). Isp: 275 sec. Burn time: 129 sec. Length: 31.60 m (103.60 ft). Diameter: 3.05 m (10.00 ft). Propellants: Solid.

• Stage1: 1 x Ariane H155. Gross Mass: 170,800 kg (376,500 lb). Empty Mass: 12,700 kg (27,900 lb). Motor: 1 x Vulcain. Thrust (vac): 1,114.000 kN (250,437 lbf). Isp: 430 sec. Burn time: 589 sec. Length: 30.50 m (100.00 ft). Diameter: 5.46 m (17.91 ft). Propellants: Lox/LH2.

• Stage2: 1 x Ariane 5 EPS L10. Gross Mass: 12,750 kg (28,100 lb). Empty Mass: 2,750 kg (6,060 lb). Motor: 1 x Aestus. Thrust (vac): 27.400 kN (6,160 lbf). Isp: 324 sec. Burn time: 1,100 sec. Length: 3.36 m (11.02 ft). Diameter: 3.96 m (12.99 ft). Propellants: N2O4/MMH.

• Stage0: 2 x Ariane 5-0. Gross Mass: 277,500 kg (611,700 lb). Empty Mass: 39,800 kg (87,700 lb). Motor: 1 x P230. Thrust (vac): 6,470.000 kN (1,454,510 lbf). Isp: 275 sec. Burn time: 129 sec. Length: 31.60 m (103.60 ft). Diameter: 3.05 m (10.00 ft). Propellants: Solid.

• Stage1: 1 x Ariane H155. Gross Mass: 170,800 kg (376,500 lb). Empty Mass: 12,700 kg (27,900 lb). Motor: 1 x Vulcain. Thrust (vac): 1,114.000 kN (250,437 lbf). Isp: 430 sec. Burn time: 589 sec. Length: 30.50 m (100.00 ft). Diameter: 5.46 m (17.91 ft). Propellants: Lox/LH2.

• Stage2: 1 x Ariane 5-2. Gross Mass: 12,500 kg (27,500 lb). Empty Mass: 2,700 kg (5,900 lb). Motor: 1 x Aestus. Thrust (vac): 27.400 kN (6,160 lbf). Isp: 324 sec. Burn time: 1,100 sec. Length: 3.36 m (11.02 ft). Diameter: 3.96 m (12.99 ft). Propellants: N2O4/MMH.

• Stage0: 2 x Ariane 5 EAP. Gross Mass: 278,330 kg (613,610 lb). Empty Mass: 38,200 kg (84,200 lb). Motor: 1 x P241. Thrust (vac): 6,470.000 kN (1,454,510 lbf). Isp: 275 sec. Burn time: 130 sec. Length: 31.60 m (103.60 ft). Diameter: 3.05 m (10.00 ft). Propellants: Solid.

• Stage1: 1 x Ariane 5 EPC. Gross Mass: 186,000 kg (410,000 lb). Empty Mass: 12,700 kg (27,900 lb). Motor: 1 x Vulcain 2. Thrust (vac): 1,114.000 kN (250,437 lbf). Isp: 434 sec. Burn time: 650 sec. Length: 30.50 m (100.00 ft). Diameter: 5.46 m (17.91 ft). Propellants: Lox/LH2.

• Stage2: 1 x Ariane 5 ESC B. Gross Mass: 27,500 kg (60,600 lb). Empty Mass: 3,400 kg (7,400 lb). Motor: 1 x Vinci. Thrust (vac): 153.900 kN (34,598 lbf). Isp: 467 sec. Burn time: 700 sec. Length: 10.00 m (32.00 ft). Diameter: 5.46 m (17.91 ft). Propellants: Lox/LH2.

Model: ADLER. Status: Study 1993.

Ariane-5 derived semi-reusable proposal of 1993. Expendable fuel tanks but recoverable propulsion/avionics module.

Model: Ariane 5 FLS.

Ariane 5 ALS Booster Credit - Mark Lindroos

Status: Study 1988.

Partially reusable concept of 1988 using Ariane 5 core with twin reusable flyback boosters.

Model: Ariane 5 RRL.

RRL Spaceplane Credit - Mark Lindroos

Status: Study 1993.

Partially reusable concept of 1993 using Ariane 5 core with flyback booster stages with Russian engines (RD-120 or RD-701).

Model: Ariane 5 VTVL. Status: Study 1995.

Partially reusable concept of 1995 using Ariane 5 core with vertical takeoff, vertical landing boosters.

1984 - Preliminary design of all-new replacement of Ariane 4 launch vehicle begins.

1988 - Full scale development of Ariane 5 launch vehicle authorised. The Ariane 5 was a completely new design, with a single-engine Lox/LH2 core stage flanked by two solid rocket boosters. Full scale development cost $ 8 billion.

1996 June 4 - 12:34 GMT - Kourou ELA3. Ariane 5G V88 (501) FAILURE: Vehicle went off course and was destroyed by range safety. Reuse of flight software from Ariane 4 was the cause (faulty program logic that only took effect on Ariane 5 launch trajectory). Cluster F1 Spacecraft: Cluster. Agency: ESA. The Cluster satellites were a series of sophisticated earth-observation platforms that were to be launched aboard the first Ariane 5. The explosion of the booster led to a costly setback for European space science. There were no back-up spacecraft. Some instruments may fly on other future satellites.

1997 October 30 - Kourou ELA3. Ariane 5G V101 (502) MAQSAT-H/TEAMSAT Spacecraft: MAQSAT. Agency: ESA. Perigee: 545 km (338 mi). Apogee: 26,504 km (16,468 mi). Inclination: 7.60 deg. Period: 465.70 min. Dummy communications satellite instrumented to report the actual payload bay environment during launch. It included the TEAMSAT technology experiment payload, developed by ESTEC

1998 October 21 - 16:37 GMT - Kourou ELA3. Ariane 5G V112 (503) Maqsat 3 Spacecraft: MAQSAT. Agency: ESA. Perigee: 1,017 km (631 mi). Apogee: 35,491 km (22,053 mi). Inclination: 7.50 deg. Period: 641.20 min. Maqsat 3 was an instrumentation package used to monitor performance of the Ariane 5 booster. At T+12:43 the Speltra adapter cover separated revealing Maqsat-3. At T+15:14 the EPS stage Aestus engine ignited and burned until T+31:00. At this point on a normal mission the satellite would separate from the EPS, but to avoid creating space debris Maqsat remained attached to the EPS. The EPS/Maqsat-3 was placed in a 1027 km x 35863 km x 7.0 degree geostationary transfer orbit.

1999 December 10 - 14:32 GMT - Kourou ELA3. Ariane 5G V119 (504) XMM Mass: 3,764 kg (8,298 lb). Spacecraft: XMM. Agency: ESA. Perigee: 7,417 km (4,608 mi). Apogee: 113,678 km (70,636 mi). Inclination: 38.80 deg. ESA's X-ray Multi-Mirror space observatory was the biggest science satellite ever built in Europe. Complementary in characteristics to NASA's Chandra satellite, the spacecraft were expected to make major new astronomical discoveries.

2000 March 21 - 23:28 GMT - Kourou ELA3. Ariane 5G V128 (505) Asiastar Mass: 2,778 kg (6,124 lb). Spacecraft: Eurostar 2000. Agency: Worldspa. Perigee: 35,772 km (22,227 mi). Apogee: 35,802 km (22,246 mi). Inclination: 0.00 deg. Direct Radio Broadcasting satelllite. First night launch of Ariane 5. Worldspace's second digital radio satellite. Joined Afristar in orbit with a mission of providing radio broadcasting to the developing world. Stationed at 105 deg E. Positioned in geosynchronous orbit at 105 deg E in 2000. As of 4 September 2001 located at 104.96 deg E drifting at 0.015 deg W per day. As of 2007 Mar 9 located at 104.99E drifting at 0.012W degrees per day.

2000 September 14 - 22:54 GMT - Kourou ELA3. Ariane 5G V130 (506) Astra 2B Mass: 3,320 kg (7,310 lb). Spacecraft: Eurostar 2000. Agency: SES. Perigee: 35,768 km (22,225 mi). Apogee: 35,804 km (22,247 mi). Inclination: 0.00 deg. Direct Broadcasting satellite. Launch postponed from July 25. Astra 2B was an Astrium/Toulouse Eurostar 2000+ television broadcast satellite owned by the Luxembourg-based Societe Europeene de Satellites. The satellite was to be stationed at 28.2E to replace the German DFS Kopernikus. It carried 28 Ku-band transponders. By September 19 Astra 2B was in a 31,153 x 35,762 km x 0.3 deg orbit, approaching geosynchronous altitude. Stationed at 28 deg E. Positioned in geosynchronous orbit at 28 deg E in 2000. As of 20 August 2001 located at 28.50 deg E drifting at 0.011 deg E per day. As of 2007 Mar 10 located at 28.15E drifting at 0.017W degrees per day.

2000 November 16 - Kourou ELA3. Ariane 5G V135 (507) PAS 1R Mass: 4,758 kg (10,489 lb). Spacecraft: HS 702. Agency: Panamsat. Perigee: 35,781 km (22,233 mi). Apogee: 35,793 km (22,240 mi). Inclination: 0.00 deg. Period: 1,436.10 min. First use of the ASAP-5 piggyback payload adapter. Communications satellite, stationed at 58 deg W. PAS 1R was a large Boeing Model 702 satellite with a dry mass of about 3000 kg (launch mass 4793 kg) and a solar panel span of 45m. It carried 36 C and 48 Ku-band transponders. PAS 1R was operated by Panamsat, whose fleet included the former Hughes Galaxy system. The PAS 1R, STRV 1c/1d, and AMSAT Phase 3D satellites were placed in orbit on a single Ariane launch. The EPS stage entered geostationary transfer orbit at 0134 GMT, followed by separation of the PAS 1R main payload. As of 4 September 2001 located at 45.03 deg W drifting at 0.016 deg W per day. As of 2007 Mar 1 located at 45.05W drifting at 0.023W degrees per day.

2000 December 20 - Kourou ELA3. Ariane 5G V138 (508) Astra 2D Mass: 1,414 kg (3,117 lb). Spacecraft: HS 376. Agency: SES. Perigee: 35,886 km (22,298 mi). Apogee: 35,895 km (22,304 mi). Inclination: 0.20 deg. Period: 1,441.41 min. Astra 2D was a Boeing 376HP spin-stabilised satellite, with a dry mass of around 700 kg. It was owned by the Luxembourg-based company SES and was to broadcast to the British Isles. Astra 2D was in a 292 x 35835 km x 2.2 deg transfer orbit on December 22 and was subsequently boosted into geosynchronous orbit by its Star 30 apogee kick motor. The 825 kg (dry mass) satellite carried 16 Ku-band transponders to provide direct-to-home voice, video, and data transmissions to Britain and neighboring countries after parking over 28.2 deg-E longitude. Positioned in geosynchronous orbit at 28 deg E in 2001 As of 3 September 2001 located at 28.17 deg E drifting at 0.014 deg E per day. As of 2007 Mar 10 located at 28.17E drifting at 0.014W degrees per day.

2001 March 8 - Kourou ELA3. Ariane 5G V140 (509) Eurobird Mass: 3,050 kg (6,720 lb). Spacecraft: Spacebus 3000. Agency: Eutelsat. Perigee: 35,773 km (22,228 mi). Apogee: 35,798 km (22,243 mi). Inclination: 0.00 deg. Period: 1,436.00 min. Launch delayed from March 2. Eurobird was a Spacebus 3000B3 built by Alcatel (Cannes). It was the 18th member of the European Eutelsat consortium's geosynchronous constellation and carried 24 Ku-band transponders to provide broad bandwidth and high power direct-to-home transmissions to enable digital entertainment and internet connections. The three tonne (with fuel) satellite was to be parked over 28.5 deg-E longitude, replacing the aging Copernicus (Kopernikus (DFS 3), 1992-066A). Dry mass was probably around 1300 kg. The satellite had an Astrium S400 bipropellant engine. Positioned in geosynchronous orbit at 28 deg E in 2001 As of 4 September 2001 located at 28.50 deg E drifting at 0.005 deg W per day. As of 2007 Mar 11 located at 28.52E drifting at 0.000W degrees per day.

2001 July 12 - 21:58 GMT - Kourou ELA3. Ariane 5G V142 (510) Artemis Mass: 3,105 kg (6,845 lb). Spacecraft: Artemis. Agency: ESA. Perigee: 32,451 km (20,164 mi). Apogee: 32,586 km (20,247 mi). Inclination: 1.10 deg. Period: 1,272.40 min. Artemis was a European Space Agency satellite designed to test new communications technologies. The Ariane 510 vehicle failed to reach its correct orbit. The solid boosters and main stage worked as planned and put the EPS upper stage in the planned near-suborbital trajectory. The EPS stage then fired but the Aestus engine failed to reach full thrust and cut off 1 minute early. Instead of the planned 858 x 35853 km orbit, only a 592 x 17528 km orbit was reached. The 3.1 tonne (with fuel), 2.5 kW spacecraft carried two pairs of ion engines and had adequate xenon propellant for those engines to reach geosynchronous altitude. This was the first ever rescue of a satellite mission using electric propulsion. The satellite reached its operational orbit in 31 January 2003.using the four German RITA electric xenon thrusters. Artemis could then function as originally planned, as there remained sufficient chemical propellant for 10 years’ operation. Artemis was to provide voice and data communications between mobile phones in Europe and North America, and act as a relay satellite between low-Earth orbiters and ground stations. Eventually, as part of the planned EGNOS system (to be operational by about 2010) it was to provide navigation/location determination as an independent European counterpart to the GPS and GLONASS fleets. As of 2007 Mar 11 located at 21.40E drifting at 0.001W degrees per day.

2002 March 1 - 01:07 GMT - Kourou ELA3. Ariane 5G V145 (511) Envisat Mass: 7,991 kg (17,617 lb). Spacecraft: Envisat. Agency: Arianespace. Perigee: 783 km (486 mi). Apogee: 785 km (487 mi). Inclination: 98.60 deg. Period: 100.50 min. This launch was the first Ariane 5 to use the 17-m Long Fairing and the first to launch north from Kourou. The booster placed the European Space Agency's Envisat polar platform in orbit. The flight profile was quite different from earlier Ariane 5 GTO launches where the EPC core stage usually reached a marginal orbit. In this case EPC separation at 350 km high 10 min after launch. The stage was on a -2610 x 651 km x 93.8 deg orbit, reaching apogee around 0125 UTC and reentering north of Ellesmere Island at about 0136 UTC. The EPS final stage with Envisat only achieved a positive perigee at 22 minutes after launch, with a circular 790 km sun-synchronous orbit reached at 25 min after launch. ESA reported the booster put the satellite to within 20 m of the desired orbital position.

2002 July 5 - 23:22 GMT - Kourou ELA3. Ariane 5G V153 (512) Ville de Charleroi Stellat 5 Mass: 4,050 kg (8,920 lb). Spacecraft: Spacebus 3000. Agency: Stellat (France). Perigee: 35,767 km (22,224 mi). Apogee: 35,807 km (22,249 mi). Inclination: 0.00 deg. Period: 1,436.10 min. Launch delayed from late June. Stellat-5 was an Alcatel Spacebus 3000B3 with a dry mass of 1805 kg and 2245 kg of propellant. The satellite carried Ku-band and C-band transponders, and was a joint venture between France Telecom and Europeon.Star which was to provide 2-way internet access and video transmission from 5 deg W. Stellat-5 was colocated with France Telecom's Telecom 2C. As of 2007 Mar 10 located at 4.99W drifting at 0.000E degrees per day.

2002 August 28 - 22:45 GMT - Kourou ELA3. Ariane 5G V155 (513) Atlantic Bird 1 Mass: 2,700 kg (5,900 lb). Spacecraft: Italsat. Agency: Eutelsat. Perigee: 35,786 km (22,236 mi). Apogee: 35,787 km (22,236 mi). Inclination: 0.10 deg. Period: 1,436.10 min. Launch delayed from August 27. Atlantic Bird was a European (EUTELSAT) geostationary communications spacecraft. The 2.7-ton (1550 kg dry with 1150 propellant), 5 kW satellite was to provide voice, video, and Internet services to Europe and the eastern part of America through its 24 transponders after being parked over 12.5° W. As of 2007 Mar 10 located at 12.49W drifting at 0.006W degrees per day.

2002 December 11 - Kourou ELA3. Ariane 5ECA V157 (517) FAILURE: The Ariane 5 core's Vulcain-2 engine began failing at T+178 seconds. The rocket veered off course and the destruct signal was sent. Hot Bird 7 Mass: 3,350 kg (7,380 lb). Spacecraft: Eurostar 2000. Agency: Eutelsat. Maiden flight of Ariane 5 EC-A. Delayed from October, November 20 and 28. Hot Bird 7, a Eutelsat geostationary communications satellite, was lost in the failed first flight of the Ariane 5 EC-A. Value of the lost satellite was Euro 250 million.

2003 April 9 - 22:52 GMT - Kourou ELA3. Ariane 5G V160 (514) Cities of Bordeaux/Colleferro Insat 3A Mass: 2,958 kg (6,521 lb). Spacecraft: Insat 3. Agency: ISRO. Perigee: 35,771 km (22,227 mi). Apogee: 35,802 km (22,246 mi). Inclination: 0.10 deg. Period: 1,436.10 min. Return to flight of Ariane 5G after grounded following Ariane 5EC-A failure. Launch delayed from February 24, April 8, 2003. Satellite also had meteorological instruments. As of 2007 Mar 10 located at 93.48E drifting at 0.009W degrees per day.

2003 June 11 - Kourou ELA3. Ariane 5G V161 (515) Optus and Defence 1 Mass: 4,725 kg (10,416 lb). Spacecraft: FS-1300. Perigee: 35,770 km (22,220 mi). Apogee: 35,803 km (22,246 mi). Inclination: 0.10 deg. Period: 1,436.10 min. Satellite jointly owned by Singtel Optus Pty and the Australian Dept. of Defense. Previous satellites in the series were purely civilian and didn't carry the dedicated defence communications equipment. Prime contractor for the satellie was Mitsubishi, using a Loral FS-1300 bus with UHF, X-band and Ka-band communications transponders. As of 2007 Mar 11 located at 109.87E drifting at 0.009W degrees per day.

2003 September 27 - 23:14 GMT - Kourou ELA3. Ariane 5G V162 (516) E-Bird Mass: 1,525 kg (3,362 lb). Spacecraft: HS 376. Agency: Eutelsat. Perigee: 664 km (412 mi). Apogee: 35,758 km (22,218 mi). Inclination: 6.90 deg. Period: 639.60 min. Last flight of the Ariane 5G. Launch delayed from July 15, August 22 and 28, September 3. The e-Bird was to service high-speed access networks providing both forward and return links via satellite. The spacecraft carried 20 active Ku-band transponders, each powered by a 33-watt traveling wave tube amplifier. The Ku-band transponders were connected to four spot beams that would provide coverage over Europe and Turkey. The spacecraft was to operate at 33 degrees East longitude, and had a contract life of 10 years.

2004 March 2 - 07:17 GMT - Kourou ELA3. Ariane 5G+ V158 (518) Rosetta Mass: 3,065 kg (6,757 lb). Spacecraft: Rosetta. Agency: ESA. Launch delayed from January 13, 2003, February 26 and 27, 2004.

2004 July 18 - 00:44 GMT - Kourou ELA3. Ariane 5G+ V163 (519) Anik F2 Mass: 5,950 kg (13,110 lb). Spacecraft: HS 702. Agency: Télésat Canada. Perigee: 33,253 km (20,662 mi). Apogee: 38,333 km (23,818 mi). Inclination: 0.20 deg. Period: 1,436.40 min. Delayed from May, July 9, 13, 16 and 17. Heaviest single payload to GTO to that date. As of 2007 Mar 11 located at 111.09W drifting at 0.004W degrees per day.

2004 December 18 - 16:26 GMT - Kourou ELA3. Ariane 5G+ V165 (520) Helios 2A Mass: 4,200 kg (9,200 lb). Spacecraft: Helios 2. Agency: DGA. Perigee: 688 km (427 mi). Apogee: 690 km (420 mi). Inclination: 98.08 deg. Period: 98.39 min. First of two new-generation French military surveillance satellites. Last flight of Ariane 5G model. Launch delayed from December 10.

2005 February 12 - 21:03 GMT - Kourou ELA3. Ariane 5ECA V164 (521) City of Bremen XTAR-EUR Mass: 3,631 kg (8,004 lb). Spacecraft: FS-1300. Perigee: 35,778 km (22,231 mi). Apogee: 35,794 km (22,241 mi). Inclination: 0.10 deg. Period: 1,436.10 min. Return to flight of Ariane 5 EC-A after booster failure on first launch. Delayed from April, June, September 28, October 28, November 3 and 8, 2004; and February 11, 2005. XTAR-EUR was a Spanish X-band military communications satellite operated by Hisdesat/XTAR of Spain. It had a dry mass of 1412 kg and 2219 kg of propellant. As of 2007 Mar 8 located at 28.95E drifting at 0.006W degrees per day.

2005 August 11 - 08:20 GMT - Kourou ELA3. Ariane 5GS V166 (523) Ipstar 1 Mass: 6,486 kg (14,299 lb). Spacecraft: FS-1300. Agency: Shin Satellite. Perigee: 35,777 km (22,230 mi). Apogee: 35,797 km (22,243 mi). Inclination: 0.00 deg. Period: 1,436.10 min. Ariane 5GS version maiden flight. Launch delayed from July 8 and 11, 2005. Heaviest geosynchronous transfer orbit payload to date. As of 2007 Mar 11 located at 119.46E drifting at 0.009W degrees per day.

2005 October 13 - 22:32 GMT - Kourou ELA3. Ariane 5GS V168 (524) Galaxy 15 Mass: 2,033 kg (4,481 lb). Spacecraft: Star bus. Agency: PanAmSat. Perigee: 35,776 km (22,230 mi). Apogee: 35,796 km (22,242 mi). Inclination: 0.10 deg. Period: 1,436.10 min. Slated to provide satellite television services to the United States market. As of 2007 Mar 10 located at 132.99W drifting at 0.009W degrees per day.

2005 November 16 - 23:46 GMT - Kourou ELA3. Ariane 5ECA V167 (522) Telkom 2 Mass: 1,975 kg (4,354 lb). Spacecraft: Star bus. Agency: PT Telkom. Perigee: 35,781 km (22,233 mi). Apogee: 35,794 km (22,241 mi). Inclination: 0.10 deg. Period: 1,436.20 min. Satellite's launch delayed from April 14, May 31, October 27, November 10 and 12, 2005, for technical problems. As of 2007 Mar 11 located at 118.00E drifting at 0.013W degrees per day.

2005 December 21 - 22:33 GMT - Kourou ELA3. Ariane 5GS V169 (525) Insat 4A Mass: 3,081 kg (6,792 lb). Spacecraft: Insat 3. Agency: ISRO. Perigee: 35,775 km (22,229 mi). Apogee: 35,798 km (22,243 mi). Inclination: 0.00 deg. Period: 1,436.10 min. Delayed from late July 2005. Launch delayed from August 23, October, November 14 and 30, December 8, 16 and 20. Dry mass 1385 kg. The satellite was equipped with Ku-band and C-band transponders and would join other Insats in providing telecommunications and television services to the Indian subcontinent. After three engine burns the satellite reached geostationary altitude over the Indian Ocean at 04:30 GMT on 26 December, then deployed its solar arrays. As of 2007 Mar 11 located at 83.00E drifting at 0.006W degrees per day.

2006 March 11 - 22:33 GMT - Kourou ELA3. Ariane 5ECA V170 (527) Spainsat Mass: 3,683 kg (8,119 lb). Spacecraft: FS-1300. Agency: Hisdesat. Perigee: 35,777 km (22,230 mi). Apogee: 35,797 km (22,243 mi). Inclination: 0.00 deg. Period: 1,436.10 min. Spainsat was to provide secure X and Ku band communications for the Spanish defense ministry. It had a dry mass of 1467 kg and a solar panel span of 31.4m. As of 2007 Mar 10 located at 29.99W drifting at 0.010W degrees per day.

2006 May 27 - 21:09 GMT - Kourou ELA3. Ariane 5ECA V171 (529) Satmex 6 Mass: 5,465 kg (12,048 lb). Spacecraft: FS-1300. Agency: SatMex. Perigee: 35,780 km (22,230 mi). Apogee: 35,794 km (22,241 mi). Inclination: 0.00 deg. Period: 1,436.10 min. The satellite had a dry mass of 2310 kg and a hybrid C-band and Ku-band telecom payload for telecom and internet service in Mexico and the rest of North and Latin America As of 2007 Mar 11 located at 113.03W drifting at 0.002W degrees per day.

2006 August 11 - 22:15 GMT - Kourou ELA3. Ariane 5ECA V172 (531) JCSAT 10 Mass: 4,048 kg (8,924 lb). Spacecraft: AS 2100. Agency: JSAT. Perigee: 35,781 km (22,233 mi). Apogee: 35,793 km (22,240 mi). Inclination: 0.00 deg. Period: 1,436.10 min. Ku/C-band television broadcasting satellite for the Japanese market; mass 1858 kg dry. As of 2007 Mar 11 located at 128.01E drifting at 0.012W degrees per day.

2006 October 13 - 20:56 GMT - Kourou ELA3. Ariane 5ECA V173 (533) DirecTV 9S Spacecraft: FS-1300. Agency: DirecTV. Perigee: 35,774 km (22,228 mi). Apogee: 35,798 km (22,243 mi). Inclination: 0.00 deg. Period: 1,436.10 min. Addition to DirecTV's direct broadcast television constellation. Carried 52 high-power Ku-band transponders and 2 Ka-band transponders. As of 2007 Mar 11 located at 101.13W drifting at 0.009W degrees per day.

2006 December 8 - 22:08 GMT - Kourou ELA3. Ariane 5ECA V174 (534) WildBlue 1 Mass: 4,735 kg (10,438 lb). Spacecraft: FS-1300. Perigee: 35,780 km (22,230 mi). Apogee: 35,792 km (22,240 mi). Inclination: 0.0200 deg. Period: 1,436.08 min. Broadband internet satellite, using the Ka-band satellite. Dry mass 2000 kg. At separation of the Ariane core the stack was in a -1282 km x 233 km x 6.9 deg suborbital trajectory. The ESC-A upper stage fired to put the satellites in a geostationary transfer orbit of 265 km x 35700 km x 2.0 deg. As of 2007 Mar 11 located at 111.14W drifting at 0.004W degrees per day.

2007 March 11 - 22:03 GMT - Kourou ELA3. Ariane 5ECA V175 (535) Skynet 5A Mass: 4,635 kg (10,218 lb). Spacecraft: Eurostar 3000. Agency: Paradigm. Perigee: 35,772 km (22,227 mi). Apogee: 35,800 km (22,200 mi). Inclination: 0.10 deg. Period: 1,436.10 min. Skynet 5A was launched by Paradigm Secure Communications as part of its turnkey contract to provide a secure communications satellite network to the British military and NATO.

2007 May 4 - 22:29 GMT - Kourou ELA3. Ariane 5ECA V176 (536) Astra 1L Mass: 4,497 kg (9,914 lb). Spacecraft: AS 2100. Agency: SES Astra. Perigee: 35,784 km (22,235 mi). Apogee: 35,788 km (22,237 mi). Inclination: 0.10 deg. Period: 1,436.00 min. Astra 1L provided direct-to-home broadcast services to Europe from its location at 19.2º East. It also strengthened the SES in-orbit backup system, extended fleet coverage from the Canary Islands eastwards up to the Russian border, and allowed Astra 2C to be moved from 19.2º East to 28.2º to fulfill high capacity demand from the U.K. and Ireland. Astra 1L was equipped with 29 Ku + 2 Ka active transponders, which would be reduced to 27 active transponders after its first five years of operation.

2007 August 14 - 23:44 GMT - Kourou ELA3. Ariane 5ECA V177 (537) Spaceway 3 Mass: 6,075 kg (13,393 lb). Spacecraft: HS 702. Agency: Hughes Network Systems. Perigee: 26,629 km (16,546 mi). Apogee: 44,893 km (27,895 mi). Inclination: 0.20 deg. Period: 1,434.80 min. Satellite launched for Hughes Network Systems, with a Ka-band payload for space-based internet. Mass 3655 kg dry.

2007 October 5 - 22:02 GMT - Kourou ELA3. Ariane 5GS V178 (526) Optus D-2 Spacecraft: Star bus. Agency: Optus. Perigee: 35,862 km (22,283 mi). Apogee: 35,889 km (22,300 mi). Inclination: 0.00 deg. Period: 1,440.70 min. Ku-band satellite designed to deliver television, internet, communications, and data services to Australia and New Zealand. After deployment of the two satellites, the EPS third stage made a brief burn at 23:28 GMT to make the first in-flight test the Aestus engine's restart capability. This was to be used in 2008 in the first launch of the ATV ISS resupply spacecraft.

2007 November 14 - 22:06 GMT - Kourou ELA3. Ariane 5ECA V179 (538) Skynet 5B Mass: 4,635 kg (10,218 lb). Spacecraft: Eurostar 3000. Agency: Paradigm. Perigee: 35,784 km (22,235 mi). Apogee: 35,789 km (22,238 mi). Inclination: 0.10 deg. Period: 1,436.10 min. Skynet 5B was designed to provide communications services in the SHF and UHF bands to the UK Ministry of Defence.

2007 December 21 - 21:41 GMT - Kourou ELA3. Ariane 5GS V180 (530) Rascom-QAF-1 Mass: 4,579 kg (10,094 lb). Spacecraft: Spacebus 4000. Agency: RascomStarQAF. Perigee: 35,771 km (22,227 mi). Apogee: 35,796 km (22,242 mi). Inclination: 0.10 deg. Period: 1,436.00 min. African communications satellite with a hybrid Ku/C-band payload. Nominal owner RascomStarQAF of Port Louis, Mauritius, a subsidiary of the Regional African Satellite Communications Organization (RASCOM) based in Cote d'Ivoire. The mission and satellite control centers were located in Cameroun and Libya. The satellite was to provide voice, data and internet services throughout Africa. Ahelium leak in the propulsion system prevented use of the primary apogee motor. Reaction control motors were used instead to slowly move the satellite into geosynchronous orbit. The satellite was expected to reach its operating location, but with a shorter-than-planned operational lifetime.

2008 March 9 - 04:03 GMT - Kourou . Jules Verne ATV Mass: 19,012 kg (41,914 lb). Spacecraft: ESA Automated Transfer Vehicle. Perigee: 336 km (208 mi). Apogee: 343 km (213 mi). Inclination: 51.60 deg. Period: 91.30 min. First launch of Europe's Automated Transfer Vehicle, a logistics vehicle designed for ISS resupply. The Ariane model 5ES launch vehicle, vehicle L528, had the enhanced EAP solid boosters and EPC core stage of the Ariane 5ECA, but with the new EPS-V upper stage with restart capability and a vehicle equipment bay instrument unit strengthened to carry the heavier LEO payload. Jules Verne carried 1300 kg of dry cargo, 302 kg of water and oxygen, and 860 kg of propellant to the ISS. For this test mission it had a dry mass of 10075 kg and 6475 kg of maneuvering propellant (in later missions the propellant could be thousands of kilograms less, in order to deliver more cargo).

The EPS stage made its first burn and placed the stack into a 137 km x 260 km orbit at 04:20 GMT. The EPS restarted at 05:05, burned for 30-seconds, and released the ATV into a 254 km x 272 km orbit.

2008 April 18 - 22:17 GMT - Kourou . Ariane 5ECA V539 Vinasat 1 Spacecraft: AS 2100. Perigee: 35,787 km (22,236 mi). Apogee: 35,789 km (22,238 mi). Inclination: 0.00 deg. Period: 1,436.20 min. First satellite launched by Vietnam. The Vietnam Post and Telecom Corporation communications satellite was equipped with C and Ku band payloads.