Ariane 5

The Ariane 5 is a European carrier rocket from the Ariane series, which was developed under contract to ESA and is operating since 1996. It is the most powerful European launcher and allows it to carry heavy payloads into orbit.

• 4.1 Ariane 5G
• 4.2 Ariane 5GS
• 4.3 Ariane 5 ECA
• 4.4 Ariane 5 ES ATV
• 4.5 Ariane 5 ES Galileo
• 4.6 Ariane 5 ME ( Ariane 5 ECB)
• 4.7 Comparison Chart

• 7.1 Failed first flight
• 7.2 Important payloads

Concept and applications

During the conference in The Hague in November 1987 ESA Ministerial Council approved the development of a first European heavy load carrier in order to be prepared for the ever-growing telecommunications satellites. At this time, the ESA could already look back on a long, successful use of the Ariane series.

The objective in the development of the Ariane 5 was higher with a total weight of up to 6.8 tons payload 60 percent for the Geostationary transfer orbit ( GTO) with only 90 % of the cost of an Ariane 44L. This corresponds to a reduction in the cost per mass unit by 44 percent.

Another scope of Ariane 5, the European space shuttle Hermes should represent the space plane should be able to be started with a distinctive European rocket. Hermes had been suspended by the rocket on a parabolic path, which would have raised with their own drive in low-Earth orbit, the space shuttle. The European Hermes project, however, was set in 1993.

Due to the structure of the Ariane 5 with a deliberately held very low number of engines at a very high reliability should be achieved. Although Hermes was never built, a manned use of the Ariane 5 was not excluded. The reliability target of the rocket stood at 99% for the single-stage variant of magnitude higher than in the Ariane 4, which had been developed only for satellite launches and many engines had. For the two-stage variant 98.5 % were targeted. Accordingly, great was the disappointment when the Ariane 5 is equal to the first flight suffered a false start, while its predecessor flew successfully.

Today launched into geostationary orbit with the Ariane 5 mainly communication satellites.

Development and sales

The Ariane 5 has been developed by aerospace companies from ESA Member States on behalf of ESA. It turned each Member State who wanted to participate in the project, financial resources available. The industry of the State in development then got orders worth the price paid by the state in development contribution of the ESA. The ESA had carried out the project of the French space agency CNES, which took over in the partner states for the technical management, financial management and the distribution of jobs to the individual companies. Therefore, the launch company Arianespace had to order at the companies selected by ESA and can be mounted by companies selected for the items of the rocket.

After the false start on the first flight of the Ariane 5 ECA in 2002, this complex system was abolished and the EADS Space Transportation (now EADS subsidiary Astrium Space Transportation ) as the main contractor. EADS is now building the rockets completely from the individual parts manufactured by it and the partner companies and is responsible for the functioning of the entire missile. It provides the rocket after the final inspection of their customers Arianespace.

For the first three starts ESA and CNES were directly responsible, Arianespace later took over the marketing. The missile is also offered to international clients to start their satellites paid (~ $ 180 million ). Almost all start relating to these customers, on the other hand starts the ESA average only about 1-2 times per year payload (s ) with the Ariane 5

The development costs of the Ariane 5 was about 5.8 billion euros (7 billion U.S. dollars). Director of the Ariane program was the German aerospace engineer Horst Holsten.

Technology

The optimized to Hermes generic Ariane 5 is called Ariane 5G ( générique ). Composed of:

• Two solid boosters ( EAP designation P238 ). These boosters are each composed of three segments, are about 30 m long ( 24.75 m segment length), have a diameter of 3.05 m, a wall thickness of 8.1 mm and each hold 238 tons of solid propellant. The top segment of the booster is the shortest and is filled already in the Italian Colle Ferro. In contrast to the other two long segments ( which are loaded only on the grid ) is designed as a star-shaped internal burner. It provides, therefore, at the start particularly good driving power that goes back strongly after the burning of the points of the star. The middle and lower segments, however, are designed as internal burner. Their thrust increases with the burning off of the inside outwards slowly, because the Abbrandfläche increases with time. The segments were until 2004, connected by a kind of plug-in connection that was backed with 180 shear bolt with 24 mm diameter and made ​​gas -tight by rubber O- rings. Today ( first use in 2006 ), they are vacuum sealed in an electron beam welding machine. The boosters have a given constantly changing shear profile with an average of 4400 kN thrust, which rises to a maximum of 6650 kN. The burning time is 130 seconds, after which they are discarded. APCP fuel is 14% of hydroxyl -terminated polybutadiene ( HTPB ), 18 % aluminum powder and 68% ammonium perchlorate. The booster housing produced by the company MT Aerospace AG in Augsburg, which establishes the current booster segments made ​​of steel, but has also produced as technology of carbon fiber, the use of which would mean a significant weight and cost reduction. The boosters are equipped in some cases for quality control with a present in the nose cap two-stage parachute return system, whereby after using a rescue from the sea is possible.

• A very large main stage ( EPC designation H158 ). My empty weight is only 12.5 tons thanks to extreme lightweight aluminum. The material is so thin that the rocket would collapse under its own weight, if one straightens the stage empty. Stability they achieved only through the filled fuel or compressed gas. It is 30.5 m high, has 5.4 m in diameter and holds 158 tons of fuel. This level has only one engine, the 605 seconds long provides a thrust of 1180 kN by the combustion of liquid hydrogen and oxygen and thus not produce enough thrust to leave the rocket liftoff without the thrust of the booster. The main stage is produced by EADS Astrium Space Transportation in Les Mureaux, France. The tanks of the main stage will be supplied from the neighboring factory of Cryospace. The Vulcain engine of the main stage is produced by a consortium of European engine companies under the leadership of the SEP.

At the start of the first rocket ignites only the main engine. After the computers have checked it for function and the engine has been running at full power, the solid rocket boosters are ignited after seven seconds and the rocket lifts off. Should be established before lifting problems with the main engine, it can be switched off without any damage. In contrast, the solid rocket boosters after ignition can not be turned off on principle, which explains this ignition sequence.

• On the main stage sits housed in a ring structure control unit which controls and monitors the flight of the Ariane 5. Immediately on this ring was originally Hermes sit and reach, after separation from the main stage with the aid of its own engines, the orbit of the space shuttle.
• Thus, the Ariane 5 can also bring satellites into GTO ( Geotransferorbit ), a very small school ( name L9.7 EPS ) was developed, which is mounted in the ring of the control unit. This stage holds 9.7 tons of fuel, which is housed in four spherical tanks. It has a compressed gas- funded engine that burns with dinitrogen tetroxide during a burn time of up to 1100 seconds Monomethylhydrazine. The pressurized helium gas is housed in two smaller spherical tanks. It is also produced by EADS-Astrium Space Transportation in Bremen. The Aestus engine is delivered from the factory of EADS Astrium Space Transportation, Ottobrunn.

Payload fairings

There are three different lengths of payload fairings are available which are manufactured by RUAG Space in Switzerland. By a pyrotechnic separation system, the payload fairings split lengthwise as well as on along the bottom edge and are discarded when the air resistance at about 110 km altitude, the cargo can not cause damage.

• The short payload fairing is 12.7 meters long. Your usable volume is 125 m³ and is together with all double launchers used.
• The medium- long payload fairing is 13.8 meters long. Your usable volume of 145 m³. She is 5 used together with the double starter Sylda.
• The long payload fairing is 17 m long. Your usable volume of 200 m³. She is 5 used together with the double starter Sylda.
• RUAG is currently developing an even longer payload fairing for the Ariane 5 ME with 18.9 m length for use on this from the year 2017.

There are also spacers, which are also produced by RUAG Space and can be used to extend all available panels. The elongation is 50 to 200 cm, corresponding to a volume of 8-33 m³. These rings are mounted below the fairing and remain on the missile.

Due to increasing volume of geostationary satellites, Arianespace has proposed to extend the payload fairing of the Ariane ECA. The French government has followed the suggestion and leaves a 2 meter long payload fairing for € 25 million to develop. It should be available in 2015.

Double starting devices

To be able to carry two larger satellites at a start into orbit, Ariane 5 is a dual launch devices, two different types are used. Each of the two types is available in several versions. They are manufactured by EADS-Astrium Space Transportation in Bremen.

The first type called Speltra is a downwardly open cylinder with 5.4 m diameter has the same diameter as the rocket. The Speltra is placed over the satellite previously attached to the upper stage of the Ariane 5. Thereafter is attached to the Speltra the second satellite, that the fairing is fitted. The payload fairing therefore sits on the Speltra. The Speltra is available for different sizes of satellites in two different lengths.

• The short Speltra is 5.7 m long and has a usable volume of 75 m³.
• The long Speltra is 7 m long and has a usable volume of 100 m³.

The advantage of Speltra is that may have the same maximum width in their satellite being transported as the satellites, which are transported directly under the fairing.

The second type called Sylda 5 is a bottom open cylinder with 4.6 m inner diameter, which is located inside the payload fairing. It is made of carbon fiber and can be easily constructed, since it must bear no aerodynamic forces. Six different length versions from 4.9 to 6.4 m in length and 50 to 65 cubic meters of usable volume are available. The second satellite is mounted on the Sylda 5, and may fill only the remaining available space in the payload fairing.

The enlargement of the Sylda 5 because of the increasing volume of satellite was inspired by Arianespace.

The Sylda 5 was derived and introduced because most satellites are not so wide that the Speltra required by a similar structure in the Ariane 4. The opposite of Speltra weight savings comes fully benefit from the payload, because the double-start device is repelled only after exposure of the upper satellite in orbit. Since the Sylda allowed 5 heavy payloads, is ( since the end of the test flights) only uses this.

Adapter for additional payloads

Finally, there is the ASAP -5 (English Ariane Structure for Auxiliary Payloads, dt about, Ariane Structure for Auxiliary Payload ' ), a device for mini or micro satellites developed and built by EADS Astrium. Also based on a similar structure of the Ariane 4, but (as with the Ariane 4) rarely used (previously the flights V135, V138, V165, V187 and without transporting satellites as ballast in V193 ). The assembly takes place at double -offs at or above the Speltra / Sylda, otherwise below the primary payload. However, Arianespace is now the ASAP - 5 is no longer a, probably because the customers of the main payloads are against the transport of additional (small ) satellite.

Versions

Even before the first flight, it was clear that the Ariane 5 would only launch satellites. The Ariane 4 dominated at the time about half of the global commercial satellite launch market and we wanted to expand this position with the Ariane 5 on. In addition, the mass of commercial communications satellites increased steadily, so that it was feared, Ariane 5 will soon be able to carry no more double -offs after their launch. Therefore, the ESA before the first start, a performance enhancement program decided. First, a significant increase in the EPS upper stage was planned so that they could take more fuel. Also, a new turbo pumps funded engine should get this changed level. However, this proposal failed in blocking the development costs by Germany.

During the ESA Council of Ministers in October 1995 in Toulouse, the extension program Ariane 5E (evolution) has been approved in order to secure the market for the increasing payloads in the telecommunications sector. The fact long-planned vehicle more efficient, the Ariane 5 ECA, Ariane 5 ECB and the Ariane 5 ES.

Until these were available, were with the Ariane 5G and Ariane 5GS two slightly modified versions developed which have a slightly increased payload capacity and are more optimized to the requirements of spacecraft and satellite launches.

Ariane 5G

The Ariane 5G differed from the Ariane 5G, except that the EPS level was slightly modified in order to increase the amount of fuel to 250 kg. In addition, other changes were made to make the step wiederzündbar and enable longer free flight phases. During the free flight phases, the new EPS L10 -called upper rotates with the load thereon about its longitudinal axis, and distributed solar radiation uniformly over the entire surface. Thus, the overheating one side of the stage and the payload and the cooling down its other side is prevented, as this may occur, a temperature difference between the two sides of 200 K (Kelvin). This procedure is in space called " barbecue " mode (note English: BBQ mode).

Ariane 5GS

The Ariane 5GS, in addition to the restartable upper stage EPS L10 new solid rocket boosters. These were under the Performance 2000 program in order ( and costs) developed by Arianespace. The program was to increase the target, the payload of the Ariane 5 through small improvements and ran on before the performance enhancement program of ESA. The EAP- P241 boosters have increased by 3 tons Treibstoffzuladung the top of the three segments and a longer exhaust nozzle made ​​of lighter materials to improve the generation of thrust at high altitudes and lower the weight. Thus, the average thrust to 5060 kN and the maximum thrust increases to 7080 kN.

The adapted from the Evolution program main stage is slightly heavier and uses a Vulcain 1B engine, which is a modified version of the Vulcain 1 engine of the Ariane 5G and 5G . However, this combination provides so much less power than the old Vulcain main stage with one that increased boosters such loss in power can not fully compensate. According to economic aspects, this seems to have been solution but to continue to produce the old main stage "better ".

Ariane 5 ECA

The Ariane 5 ECA can carry 9.6 tons with a much larger payload than its predecessor versions. The addition ECA stands for Evolution Cryotechnique Type A. It has a modernized first stage with the new Vulcain 2 engine and the new cryogenic upper stage ESC-A (Bunk Supérieur Cryotechnique Type A - Type A cryogenic upper stage ).

The modernized main stage with the newly designed thrust increased Vulcain -2 engine includes a shift in the tank by the false floor now 173 tons of fuel and is called EPC H173.

The new ESC- A H14, 4 used employed in the third stage of Ariane 4 HM -7B engine that provides a higher thrust than the previous high school and is not wiederzündbar. This allows heavier payloads and more fuel to be carried. The Treibstoffzuladung is now at 14.6 tons. Through the use of hydrogen as a combustion support the payload capacity of Ariane 5 ECA is 9.6 tons of payload in a single start and 9.1 tonnes on a double launch. It is thus much higher than that of the previous Ariane 5, wherein only a slight rise in manufacturing cost. The Ariane 5 ECA is to achieve a payload of 9.2 tonnes and 9.5 tonnes by the end of 2011 by the end of 2010 performance increases for double -offs. The tank also virtually taken over unchanged except for an extension of the Ariane 4 for the oxidizer ( oxygen) is surrounded by new, nearly hemispherical fuel tank for the hydrogen. This has, so that there is a space the shape of a thick ball socket between it and the oxygen tank. The step has a diameter of 5.4 meters. The control unit is located now at the upper level and is structurally lighter than the version used in the EPS upper stages, because they no longer have to carry in their sedentary level. The ESC A-stage also includes the adapter part of the intermediate stages, which encloses the exhaust nozzle of the HM- 7B engine. In the staging of this part of the upper left to reduce weight at the EPC and only the actual high school continues to fly.

The Ariane 5 ECA has therefore been primarily developed as an interim solution until the appearance of the Ariane 5 ECB, for launches to GTO.

Also, the maiden flight of the Ariane 5 ECA failed on 11 December 2002. The cause of the structural failure of the nozzle of the Vulcain -2 engine was found. One consequence of the failure was that the planned for January 13, 2003 Start of the Rosetta mission had to be postponed because of the risk of a total loss is now estimated to be too high.

In the modified after the false start Ariane 5 ECA is now an improved Vulcain -2 engine is used, wherein the nozzle has been reinforced and slightly shortened. In addition, the coolant flow rate was increased and she received a special heat protection of zirconia. The improved engines were - tested in Lampoldshausen in a new vacuum chamber of the DLR - also because of malfunction during the first flight.

A large part of the required for the re-qualification of the Ariane 5 ECA money should have been spent for the construction of these test stands.

A framework contract for 30 Ariane 5 ( PA batch ) with a total value of three billion Euros was concluded on 10 May 2004. He should make it possible to rationalize production and the Ariane 5 ECA to strengthen against the Russian competition.

The second successful launch of the Ariane 5 ECA took place on February 12, 2005.

Following a letter of intent from the Paris Air Show 2007, Arianespace has ordered 30 January 2009 a further 35 Ariane 5 ECA ( production lot PB) for more than 4 billion euros the main contractor EADS-Astrium. These have been used since the end of 2010, as the Ariane 5 of the PA batch are consumed.

Ariane 5 ES ATV

This version of the Ariane 5 is used to transport the European supply ship Automated Transfer Vehicle (ATV ) for ISS. The pressurized ATV provides freight, water, nitrogen, oxygen and fuel. Also, the ATV to carry away waste and increase the space station, in order to counteract the decrease of the braking effect of the atmosphere.

Overall, the Ariane 5 ES ATV can carry up to 21 tons of payload into a low Earth orbit, which corresponds to a payload of eight tons for a geostationary orbit. The rocket was the first step, the EPC H173 using the improved Vulcain -2 engine and as a second stage, a specially for the inserts with the ATV modified version of the restartable upper stage EPS - EPS -V, where the ATV is attached.

The EPS - V upper stage is ignited in a typical flight three times. The first ignition is carried out after the burning of the first stage. Thereafter, the second stage is switched off and it begins a ballistic phase in the elliptical transfer orbit. In the apogee engine is fired a second time to switch at this level on a approximately circular low earth orbit. The third stage is the ignition so far slowed down after the separation of the ATV, that it enters into an elliptical orbit whose perigee is in the atmosphere. Then when passing through the perigee it burns up in the atmosphere.

The ATV lifts after the separation of the EPS - V upper stage its orbit with its own engines to the ISS orbit to.

Ariane 5 ES Galileo

This version has been adapted for the transport of satellites in medium-high circular orbits version of the Ariane 5 ES ATV. You should expose four satellites of the European Galileo satellite navigation system at one time in their 23,616 km high circular orbit with 56 ° inclination to the equator.

The four satellites are placed in a dispenser mounted on the missile in space. Here are located on two sides of the dispenser two satellites above the other .. After reaching orbit, they are then repelled to the side. EADS Astrium has been entrusted with the development of the Ariane 5 ES Galileo on February 2, 2012. You should go into operation in 2014

Ariane 5 ME ( Ariane 5 ECB)

The cost of a second test flight of the Ariane 5 ECA and the rectification of the launch vehicle led to the development of even more powerful ESC- B for the version of Ariane 5 was initially not pursued ECB in 2003. After a successful second test flight of the Ariane 5 ECA in February 2005, EADS wanted to give up the development of the Ariane 5 ECB, as they estimated that the lying by the then planning at 12 tons GTO payload capacity of Ariane 5 ECB exceed the requirements of the commercial satellite launch market would, and therefore the relatively high development costs would not be economically justifiable. This opinion has the EADS revised in February 2006, and the chief of EADS Space Transportation, said in an interview with the FTD by an error. However, since the ESA funded the development of the Ariane 5, the final decision on these proposals by the Council of Ministers of ESA is made. At the meeting of the ESA Council of Ministers in December 2005, no official decision on the Ariane 5 ECB fell. So rested the development of ESC -B upper stage. Instead, project studies on a future European support system were adopted. Presumably, these studies lead to the development of a new carrier system, with the intermediate step of ESC -B upper stage for the Ariane 5 was also at the meeting of the ESA Ministerial Council in December 2008, no decision on the Ariane 5 ECB, the Vinci engine but further developed. Final decisions should be made at the Ministerial Council Meeting 2011 on the Ariane 5 ECB.

However, the ESA awarded as early as 20 December 2009, a contract for pre-development work on the new upper stage and other upgrades at EADS Astrium. This work is being carried under the name " Ariane 5 Midlife Evolution ( Ariane 5 ME) ". However, it would also have been possible that 2011 is the development of a new, smaller launch vehicle had been adopted, which is tailored specifically to the needs of future ESA missions for which an Ariane 5 would be too great. As a result of several years of delays, the cost of developing the ESC -B upper stage have risen sharply. When development was stopped in 2003, 699.14 million euros were for or provided. The design for the resumption starts from 1,100 million euros. Add to this the funds were spent 2003-2011. Was actually decided at the meeting of the ESA Council of Ministers on 20th - 21st November 2012, however, only the development of the Ariane 5 ME resume and reconcile with studies of the Ariane 6 to use as many of the developments for both carriers can. In 2014, then started the final common Ariane 5 ME and Ariane 6 program. For this purpose, EADS-Astrium was awarded by ESA on January 30, 2013 an order for 108 million euros to determine the exact design of the Ariane 6 and for continuing the work on the Ariane 5 ME.

The new ESC- B is for the H173 main stage of the Ariane 5 of adequate size and capacity. The ECB upper stage has a diameter of 5.4 meters and nested tanks for the oxidizer (oxygen ) and fuel ( hydrogen). The hydrogen tank is naturally about twice as large as the tank and surrounding oxygen. The two tanks are separated by an intermediate floor. The Treibstoffzuladung the ESC -B upper stage should be 28.2 tons according to current plans. You will receive a completely newly developed engine called Vinci. It is wiederzündbar and used - in contrast to the Vulcain and HM -7B engines - the main stream method. Vinci, the engine 180 generates kN of thrust and having an extensible thrust nozzle, the fuel in order to utilize as efficiently as possible. The payload capacity of the Ariane 5 ECB however, will be lower than originally planned. It should according to current plans can bring 11.2 to 11.6 tonnes into geostationary transfer orbit. The ESA specifies 11.5 tonnes, with level enough fuel reserves for a second ignition ( a short time later ) has to perform more mission types (eg, "direct deorbiting ", ie rapid return of the GTO in the Earth's atmosphere, as well as other mission types ).

Comparison Chart

Note:

* Sits in the instrument unit of 5.4 m diameter

• ELA -3 = L' Ensemble de Lancement Ariane launch site = Third Ariane
• EAP = étage d' Acceleration à Poudre = solid rocket boosters
• EPC = Étage Principal Cryotechnique = cryogenic main stage
• EPS = étage à propellant Stock Ables = upper with lagerbarem fuel
• ESC-A = Etage Supérieur de Cryotechnique type A = A cryogenic upper stage of type A
• ESC B = Etage Supérieur de Cryotechnique type B = A cryogenic upper stage of type B

Launch facilities

All Ariane 5 launches will take place from Guiana Space Centre in Kourou, French Guiana, instead. For the launch of the Ariane 5 was a dedicated launch site - ELA -3 - furnished with associated facilities for the launch preparations to allow up to ten launches per year. The entire launch preparations last 21 days. To keep the cost low at the launch site, is - in contrast to the Ariane 4 - installed the payload in the rocket just six days before the start. The missile is transported about 30 hours before the start of the ramp.

Due to the simplified Home Concept big launch pads to supply the rocket with fuel are not required. In addition, the susceptibility to disorders prior to starting reduced.

In the planned launch preparations for the area, there are four main buildings:

• In Bâtiment d' intégration Propulseur (GDP ), the solid rocket boosters mounted and checked;
• In the Bâtiment d' intégration Lanceur ( BIL), the main stage will be erected on the mobile launch table and the boosters attached;
• In the Bâtiment d' Assemblage Final ( BAF ), the payload devices assembled and erected, the tanks of the upper filled (not at cryogenic upper stages ) and carried out the final electrical inspections;
• From the Start Center Centre de Lancement n ° 3 (CDL -3), the start commands are found.

In 2000, a second movable launch pad was added to the launch complex. 2001, a new system (S5 ) for clearance of up to four payloads simultaneously was built on 3,000 sqm. Envisat was the first satellite, which they used.

Launch preparations and launch into geostationary transfer orbit ( GTO)

The launch preparations begin that about 1-2 months before the scheduled start, the main stage, the upper stage and the payload fairing, packed in large containers that arrive by ship at the port of Kourou. From there they are placed on the spaceport in their shipping containers on flat bed trucks.

The next day, the assembly begins. The main stage is lifted from its transport container. Vertical hanging on the crane being moved on the launch table. The next day the already assembled solid rocket boosters be moved and attached to the main stage left and right.

The two packed in shipping containers satellites that are to be transported in this startup are (mostly Antonov An-124 ) delivered each in its own large-capacity transport aircraft at the airport in Cayenne. From there they are taken to the spaceport. Here the satellites are discharged, technically checked and usually fueled at the end of fuel.

Meanwhile, go to the installation work on the rocket further.

• The Ariane 5GS the ring is mounted to the control unit on the main stage as the next step. The next day the EPS upper stage, which is mounted in the instrument ring follows.

• The Ariane 5 ECA instead was the ESC-A upper stage mounted as the next step on the main stage and the next day on her instrument panel. Since flight V179, the ESC-A upper stage and instrument unit is already assembled into a unit of Astrium delivered in Bremen and mounted on the main stage, so that the assembly of the Ariane 5 ECA is accelerated and simplified.

Then the rocket from BIL is transferred to the BAF, where the combined preparations of the rocket and payload start. The first satellite is mounted on the double- starting device. About him the payload fairing is mounted. Thereafter, the second satellite is mounted on the upper level. About him the combination is placed in the payload fairing, satellite and double starter. Now, even - if available - the EPS upper stage fueled with 10 tons storable fuel. Then the rocket from the BAF is taxiing to the ramp and about 11 hours long countdown can begin.

The countdown is primarily focused at the main stage, and - if present - to fuel the ESC-A upper stage with liquid oxygen and hydrogen, and to test all major systems again. 7 minutes before the start assumes the computer control. When the countdown reaches zero, ignites the engine of the main stage and will be ramped up to maximum thrust. After it has reached full thrust, it is checked by the computer system is functioning correctly. If everything is OK, ignite the solid rocket boosters and reach within 0.3 seconds full thrust. The rocket takes off. A few seconds after liftoff, the rocket from vertical ascent goes into a sloping ascent towards the Atlantic Ocean. About 120 seconds after liftoff, the solid rocket boosters burn out and are jettisoned. About 180 seconds after launch, the rocket is more than 100 km high and the payload fairing is jettisoned. It falls into the Atlantic. The rocket rises through the momentum that she has experienced through her ​​strong solid rocket boosters, further to a peak altitude of about 130 km. Now she falls, almost parallel to the earth's surface accelerating again to about 115 miles from because their speed is still suborbital. After 605 seconds the main stage of the Ariane 5 GS has burned out and is removed. They encircled almost once the earth occurs off the west coast of South America back into the Earth's atmosphere and burns up. The Ariane 5 ECA and ESV, however, the main stage has burned out after 590 seconds and is separated, flies on a parabolic path over only a part of the Atlantic and burns up before the west coast of Africa.

After separation of the main stage, the EPS or ESC A sixth ignites and continues to accelerate. The Ariane 5 GS for more than 1100 seconds burning time reaches the EPS upper stage together with their payload in about 1000 km above the geostationary transfer orbit. The Ariane 5 ECA, the ESC-A upper stage in about 600-700 km altitude reached its payload other about 970 seconds burning time geostationary transfer orbit. In both then the engine being shut down by the navigation system. Now, the senior is realigned with the person sitting on their payload and repelled the top sitting on the double starter Satellite gently. After a few minutes, when the satellite is removed from the swivel range of the upper level, this is again realigned and repels the double starter. A few minutes later, the upper is aligned again and pushes the second, usually smaller and lighter, Satellite gently.

The achieved Geostationary transfer orbit usually has. Ariane 5 GS in a planned height of about 570-35890 km and an orbital inclination of 7 ° However, a deviation of ± 10 km at perigee and ± 80-100 km at apogee and ± 0.5 ° orbital inclination is still permitted. The Ariane 5 manages mostly to achieve the planned path heights up to a few km due and the orbital inclination to the Equator at only a few hundredths to tenths of a degree.

The Geostationary transfer orbit has the highest payload in the Ariane 5 ECA about a planned height of about 250-35890 km and an orbital inclination of 7 °. However, because in many starts the payload does not exploit the full payload capacity of Ariane 5 ECA, then the remaining available capacity is utilized to deal with less than 7 ° inclination to fly a GTO ( down to 2 °). Of these, the satellite requires less fuel to accomplish geostationary orbit. This is their life benefit. As with the Ariane 5 GS, however, a deviation of ± 10 km at perigee and ± 80-100 km at apogee and ± 0.5 ° orbital inclination is still allowed even when the Ariane 5 ECA. The Ariane 5 ECA manages usually to achieve the planned path heights up to a few kilometers accurate and the orbital inclination to the Equator at only a few hundredths to tenths of a degree.

Previous offs

Since 1996, the Ariane 5 is in use. The first years of the Ariane 5 was used in parallel with the earlier Ariane 4. After the recent launch of the Ariane 4 on 15 February 2003, the Ariane 5 was until the launch of the Vega 2012, the only active launcher Europe. Most payloads are communications satellites that will be sold in geostationary transfer orbits.

Failed first flight

The Ariane 5 was launched on 4 June 1996 for its maiden flight V88. After exactly 36.7 seconds, the rocket blew itself together with its payload, the four Cluster satellites, after they began to break apart due to the aerodynamic loads of an extreme change of course. It turned out that the software is acquired in parts of the Ariane 4 did not meet the necessary requirements. The Ariane 5 accelerates faster than Ariane 4 This led to an overflow of a variable of the steering system. This bug occurred when converting a 64 -bit floating-point number for the horizontal velocity in a signed 16 - bit integer. The result was a crash of the steering system, which meant that the navigation system sent only status data to the navigation computer. This interpreted the data as a real flight, which departed considerably from the planned course, and let the exhaust nozzle of the booster pan until it stops. Thus, the rocket began to break apart and the onboard neutralization system triggered the self-destruct before the ground control could intervene. Unfortunate thing was that the faulty part of the software for the Ariane 5 was not needed at all and served only to control a start abort at the last second in the Ariane 4.

Fortunately, no lives were lost, but the material damage amounted to about 370 million U.S. dollars, which is the false start is one of the most expensive software failure in history. The first successful launch took place on 30 October 1997.

Important payloads

The hitherto most massive payload was the ESA - supply spacecraft ATV -4 for the International Space Station with 19,887 t off weight, which was exposed to the equator inclined by an Ariane 5 ES ATV in a 51.6 ° orbit at about 260 km altitude on June 5, 2013.

The environmental satellite Envisat ESA, was successfully transported on February 28, 2002 by an Ariane 5G in a sun-synchronous orbit, weighed 8.2 tonnes. On 1 July 2009, the 6.9 tonnes up to that heaviest civilian communications satellite TerreStar 1 by an Ariane 5 ECA was successfully launched into geostationary transfer orbit. The GTO record ( total mass per flight ) is 10,317 tons and was set up by an Ariane 5 ECA on February 7, 2013, the satellite Amazonas 3 and Azerspace/Africasat-1a on board.

Also two space probes - SMART -1 to the moon and Rosetta to comet Churyumov- Gerasimenko - were launched by an Ariane 5 Ariane 5 G G or.

On 14 May 2009, an Ariane 5 ECA launched the Herschel and Planck in a highly eccentric orbit 270-1197080 km altitude, which is inclined 5.99 ° to the equator. From the apogee of this orbit, the telescope maneuvered into orbit around the Lagrange point L2.

Ariane 5 as a prestige object

In order to be competitive on the world market, subsidizes the ESA with the program starts EGAS Ariane 5

In France, the Ariane is considered in the light of a national participation rate of over 50 percent as a predominantly French project. The Ariane 5 is therefore important - far more than in Germany - as a national prestige project. Is not unusual that the Ariane 5 as a metaphor for technological excellence, which testifies about a picture of the rocket in the French passports.

In the Museum Cité de l' espace in Toulouse, the space travel and research is devoted to a model of Ariane 5 is in its original size.

Ariane 5 Next Development Studies

The Ariane 5 heavy-lift derivative is a study of the CNES from the year 1991., It is discussed the possible increase in performance of the launch vehicle. The first stage (English cryogenic lower stage ) has a diameter of 8.2 meters and is equipped with five Vulcain II engines. The second stage (English cryogenic upper stage ) has a diameter of 5.4 meters and is equipped with a restartable Vulcain engine with 700 kN thrust. The possible payload capacity of 90 tons in LEO and 35 tons in lunar orbit. The study noted that the development of the Ariane 5 heavy-lift derivative would be connected, despite the use of proven technologies with high costs.