![]() It took the European Space Agency 10 years and $7 billion to produce Ariane 5, a giant. It was running the same software. This bug belongs to a species that. NIST report, “The Economic. Major failures: Ariane 5 explosion, Mars Polar Lander, Intel’s Pentium FDIV bug. Insufficient testing of safety-critical software. Software Bug destroys 500. explosion and in two weeks issued a report. Code from the Ariane 4 launch system that had been reused in the Ariane 5 trigger a bug in. Ariane 5 - Wikipedia. Ariane 5. 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, Arianespace and CNESCountry of origin. Cost per launch$1. M[1]Size. Height. Diameter. 5. 4 m (1. Mass. 77. 7,0. 00 kg (1,7. Stages. 2Capacity. Payload to LEO (2. G: 1. 6,0. 00 kg (3. ES: over 2. 0,0. 00 kg (4. Payload to GTOG: 6,9. G+: 6,9. 50 kg (1. GS: 6,1. 00 kg (1. ECA: 1. 0,5. 00 kg (2. June 2. 01. 7[3]Associated rockets. Family. Ariane. Comparable. Launch history. Status. Active. Launch sites. Guiana Space Centre. ELA- 3. Total launches. Failures. 2 (G: 1, ECA: 1)Partial failures. G)First flight. G: 4 June 1. G+: 2 March 2. 00. GS: 1. 1 August 2. ECA: 1. 1 December 2. ES: 9 March 2. 00. Last flight. G: 2. September 2. 00. 3G+: 1. December 2. 00. 4GS: 1. December 2. 00. 9ECA: 2. June 2. 01. 7ES: 1. November 2. 01. 6Notable payloads. Boosters (G, G+) – EAP P2. No. boosters. 2Length. Diameter. 3. 0. 6 m (1. Gross mass. 27. 0 tonnes (3. Engines. P2. 38. Thrust. N (1,4. 90,0. 00 lbf)Total thrust. N (3,0. 00,0. 00 lbf)Burn time. Fuel. AP, Al, HTPBBoosters (GS, ECA, ES) – EAP P2. No. boosters. 2Length. Diameter. 3. 0. 6 m (1. Empty mass. 33 tonnes (3. Gross mass. 27. 3 tonnes (3. Engines. P2. 41. Thrust. N (1,5. 90,0. 00 lbf)Total thrust. N (3,1. 80,0. 00 lbf)Burn time. Fuel. AP, Al, HTPBCore stage (G, G+, GS) – EPC H1. Length. 23. 8 m (7. Diameter. 5. 4 m (1. Empty mass. 12,2. Gross mass. 17. 0,5. Engines. G, G+: Vulcain 1. GS: Vulcain 1. BThrust. N (2. 28,0. 00 lbf) (vacuum)Specific impulse. Burn time. 60. 5 s. Fuel. LH2 / LOXCore stage (ECA, ES) – EPC H1. Length. 23. 8 m (7. Diameter. 5. 4 m (1. Empty mass. 14,7. Gross mass. 18. 4,7. Engines. Vulcain 2. Thrust. 96. 0 k. N (2. N (3. 10,0. 00 lbf) (vacuum)Specific impulse. Burn time. 54. 0 s. Fuel. LH2 / LOXSecond stage (G) – EPS L9. Length. 3. 4 m (1. Diameter. 5. 4 m (1. Empty mass. 1,2. 00 kg (2,6. Gross mass. 10,9. Engines. Aestus. Thrust. N (6,1. 00 lbf)Burn time. Fuel. MMH / N2. O4. Second stage (G+, GS, ES) – EPS L1. Length. 3. 4 m (1. Diameter. 5. 4 m (1. Empty mass. 1,2. 00 kg (2,6. Gross mass. 11,2. Engines. Aestus. Thrust. N (6,1. 00 lbf)Burn time. Fuel. MMH / N2. O4. Second stage (ECA) – ESC- ALength. Diameter. 5. 4 m (1. Empty mass. 4,5. 40 kg (1. Gross mass. 19,4. Engines. HM7. BThrust. N (1. 5,0. 00 lbf)Specific impulse. Burn time. 94. 5 s. Fuel. LH2 / LOXAriane 5 is a European heavy- lift launch vehicle that is 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. Airbus Defence and Space is the prime contractor for the vehicles, leading a consortium of other European contractors. Ariane 5 is operated and marketed by Arianespace as part of the Ariane programme. The rockets are launched by Arianespace 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 Hermes spaceplane, 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. As of July 2. 01. Arianespace has signed contracts for Ariane 5 ECA launches up till 2. Ariane 6 in 2. 02. On 2. 8 June 2. 01. Ariane 5 performed its 8. Vehicle description[edit]Cryogenic main stage[edit]Ariane 5’s cryogenic H1. H1. 58 for Ariane 5 G, G+, and GS) is called the EPC (Étage Principal Cryotechnique—Cryotechnic Main Stage). It consists of a large tank 3. Vulcain 2 engine at the base with a vacuum thrust of 1,3. The H1. 73 EPC weighs about 1. After the main cryogenic stage runs out of fuel, it can re- enter the atmosphere for an ocean splashdown. Solid boosters[edit]Attached to the sides are two P2. P2. 38 for Ariane 5 G and G+) solid rocket boosters (SRBs or EAPs from the French Étages d’Accélération à Poudre), each weighing about 2. They are fueled by a mix of ammonium perchlorate (6. HTPB (1. 4%). They each burn for 1. 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. 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 2. The French M5. 1SLBM shares a substantial amount of technology with these boosters. In February 2. 00. 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[edit]The second stage is on top of the main stage and below the payload. The Ariane 5 G used the EPS (Étage à Propergols Stockables—Storable Propellant Stage), which is fueled by monomethylhydrazine (MMH) and nitrogen tetroxide. It also has 1. 0 tonnes of storable propellants. The EPS was improved for use on the Ariane 5 G+, GS, and ES. Ariane 5 ECA uses the ESC (Étage Supérieur Cryotechnique—Cryogenic Upper Stage), which is fueled by liquid hydrogen and liquid oxygen. The EPS upper stage is capable of multiple ignitions, first demonstrated during flight V2. October 2. 00. 7. 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 2. Automated Transfer Vehicle 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. Fairing[edit]The payload and all upper stages are covered at launch by a fairing, which is jettisoned once sufficient altitude has been reached (typically above 1. The Fairing is also used for aerodynamic stability and protection from heating during supersonic flight and acoustic loads. Variants[edit]Legend for launch system status in below table: [retired] — [cancelled] — [operational] — [under development]Variant. Description. GThe original version is dubbed Ariane 5 G (Generic) and had a launch mass of 7. Its payload capability to geostationary transfer orbit (GTO) was 6,9. It flew 1. 7 times with one failure and two partial failures.[1. G+The Ariane 5 G+ had an improved EPS second stage, with a GTO capacity of 7,1. It flew three times in 2. GSAt the time of the failure of the first Ariane 5 ECA flight in 2. 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 5 GS. 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.[1. Ariane 5 GS could carry a single payload of 6,6. GTO. The Ariane 5 GS flew 6 times from 2. ECAThe Ariane 5 ECA (Evolution Cryotechnique type A), first successfully flown in 2. 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 2,1. HM- 7. B engine burning 1.
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