Ariane 4: Difference between revisions
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imported>Tigerdude9 More English spelling. |
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| image = Ariane42P rocket.png | | image = Ariane42P rocket.png | ||
| caption = The 52nd Ariane 4 carrying the [[TOPEX/Poseidon]] satellite. | | caption = The 52nd Ariane 4 carrying the [[TOPEX/Poseidon]] satellite. | ||
|function = Expendable [[launch vehicle]] | |function = Expendable [[launch vehicle]] | ||
| Line 25: | Line 24: | ||
|kilos = {{cvt|2000|–|4300|kg}} | |kilos = {{cvt|2000|–|4300|kg}} | ||
}} | }} | ||
| family = [[Ariane (rocket family)|Ariane]] | |||
| derived_from = [[Ariane 3]] | |||
| derivatives = [[Ariane 5]] | |||
|status = Retired | |status = Retired | ||
|sites = [[ | |sites = [[Guiana Space Centre|Guiana]], [[ELA-2]] | ||
|launches = 116 | |launches = 116 (40:{{nbsp}}7, 42P:{{nbsp}}15, 42L:{{nbsp}}13, 44P:{{nbsp}}15, 44LP:{{nbsp}}26, 44L:{{nbsp}}40) | ||
|success = 113 | |success = 113 (40:{{nbsp}}7, 42P:{{nbsp}}14, 42L:{{nbsp}}13, 44P:{{nbsp}}15, 44LP:{{nbsp}}25, 44L:{{nbsp}}39) | ||
|fail = 3 ( | |fail = 3 (42P:{{nbsp}}1, 44LP:{{nbsp}}1, 44L:{{nbsp}}1) | ||
|first= | |first=15 June 1988 | ||
|last=15 February 2003 | |||
|last= | |||
|stagedata = | |stagedata = | ||
{{Infobox Rocket/Stage | {{Infobox Rocket/Stage | ||
| Line 54: | Line 42: | ||
|number = 0, 2 or 4 | |number = 0, 2 or 4 | ||
|engines = [[Viking (rocket engine)|Viking 6]] | |engines = [[Viking (rocket engine)|Viking 6]] | ||
|thrust = {{cvt|752 | |thrust = {{cvt|752|kN}} | ||
|total = <!--total thrust for all boosters in kN, optional--> | |total = <!--total thrust for all boosters in kN, optional--> | ||
|alt-total = <!--total thrust for all boosters in pounds-force, optional--> | |alt-total = <!--total thrust for all boosters in pounds-force, optional--> | ||
|SI = 278 | |SI = {{cvt|278|isp}} | ||
|burntime = 142 seconds | |burntime = 142 seconds | ||
|fuel = | |fuel = {{chem2|N2O4|link=dinitrogen tetroxide}}{{nnbsp}}/{{nnbsp}}[[UDMH]] | ||
}} | }} | ||
{{Infobox Rocket/Stage | {{Infobox Rocket/Stage | ||
| Line 68: | Line 56: | ||
|number = 0, 2 or 4 | |number = 0, 2 or 4 | ||
|engines = <!--number and type of engines used on each individual booster/stage, required--> | |engines = <!--number and type of engines used on each individual booster/stage, required--> | ||
|thrust = {{cvt|650|kN | |thrust = {{cvt|650|kN}} | ||
|total = <!--total thrust for all boosters in kN, optional--> | |total = <!--total thrust for all boosters in kN, optional--> | ||
|SI = <!--specific impulse of an individual booster/stage, in secs, optional--> | |SI = <!--specific impulse of an individual booster/stage, in secs, optional--> | ||
| Line 78: | Line 66: | ||
|stageno = First | |stageno = First | ||
|name = L220 | |name = L220 | ||
|engines = 4 [[Viking (rocket engine)|Viking 5C]] | |engines = 4{{nnbsp}}×{{nnbsp}}[[Viking (rocket engine)|Viking 5C]] | ||
|thrust = {{cvt| | |thrust = {{cvt|3034|kN}} | ||
|SI = {{cvt|278|isp}} | |||
|SI = 278 | |||
|burntime = 205 seconds | |burntime = 205 seconds | ||
|fuel = | |fuel = {{chem2|N2O4|link=dinitrogen tetroxide}}{{nnbsp}}/{{nnbsp}}[[UDMH]] | ||
}} | }} | ||
{{Infobox Rocket/Stage | {{Infobox Rocket/Stage | ||
| Line 89: | Line 76: | ||
|stageno = Second | |stageno = Second | ||
|name = L33 | |name = L33 | ||
|engines = 1 [[Viking (rocket engine)|Viking 4B]] | |engines = 1{{nnbsp}}×{{nnbsp}}[[Viking (rocket engine)|Viking 4B]] | ||
|thrust = {{cvt| | |thrust = {{cvt|721|kN}} | ||
|SI = {{cvt|296|isp}} | |||
|SI = 296 | |||
|burntime = 132 seconds | |burntime = 132 seconds | ||
|fuel = | |fuel = {{chem2|N2O4|link=dinitrogen tetroxide}}{{nnbsp}}/{{nnbsp}}[[UDMH]] | ||
}} | }} | ||
{{Infobox Rocket/Stage | {{Infobox Rocket/Stage | ||
| Line 101: | Line 87: | ||
|stageno = Third | |stageno = Third | ||
|name = H10 | |name = H10 | ||
|engines = 1 [[HM7-B]] | |engines = 1{{nnbsp}}×{{nnbsp}}[[HM7-B]] | ||
|thrust = {{cvt|62. | |thrust = {{cvt|62.7|kN}} | ||
|SI = {{cvt|446|isp}} | |||
|SI = 446 | |||
|burntime = 759 seconds | |burntime = 759 seconds | ||
|fuel = | |fuel = {{chem2|LH2|link=liquid hydrogen}}{{nnbsp}}/{{nnbsp}}[[LOX]] | ||
}} | }} | ||
}} | }} | ||
The '''Ariane 4''' was a European [[ | The '''Ariane 4''' was a European [[Expendable launch system|expendable]] [[launch vehicle]] in the [[Ariane (rocket family)|Ariane family]], developed by the {{lang|fr|[[CNES|Centre national d'études spatiales]]}} (CNES), the [[Government of France|French]] space agency, for the [[European Space Agency]] (ESA). The manufacturing of the launch vehicle was led by [[Aérospatiale]] and it was marketed by [[Arianespace]]. Since its first flight on 15 June 1988 until the final flight on 15 February 2003, it attained 113 successful launches out of 116 total launches. | ||
In 1982, the Ariane 4 program was approved by ESA. Drawing heavily upon the preceding [[Ariane 3]], it was designed to provide a launcher capable of delivering heavier payloads and at a lower cost per kilogram than the earlier members of the Ariane family. The Ariane 4 was principally an evolution of the existing technologies used, as opposed to being revolutionary in its design ethos; this approach quickly gained the backing of most ESA members, who funded and participated in its development and operation. Capable of being equipped with a wide variety of [[Booster (rocketry)|strap-on booster]]s, the Ariane 4 gained a reputation for being an extremely versatile launcher. | In 1982, the Ariane 4 program was approved by ESA. Drawing heavily upon the preceding [[Ariane 3]], it was designed to provide a launcher capable of delivering heavier payloads and at a lower cost per kilogram than the earlier members of the Ariane family. The Ariane 4 was principally an evolution of the existing technologies used, as opposed to being revolutionary in its design ethos; this approach quickly gained the backing of most ESA members, who funded and participated in its development and operation. Capable of being equipped with a wide variety of [[Booster (rocketry)|strap-on booster]]s, the Ariane 4 gained a reputation for being an extremely versatile launcher. | ||
| Line 118: | Line 103: | ||
== Development == | == Development == | ||
=== Origins === | === Origins === | ||
In 1973, eleven nations decided to pursue joint collaboration in the field of space exploration and formed a new pan-national organisation to undertake this mission, the [[European Space Agency]] (ESA).<ref name="harvey-2003">{{cite book |first=Brian |last=Harvey |title=Europe's Space Programme: To Ariane and Beyond |year=2003 |publisher=Springer Science & Business Media |isbn=1-8523-3722-2 }}</ref>{{ | In 1973, eleven nations decided to pursue joint collaboration in the field of space exploration and formed a new pan-national organisation to undertake this mission, the [[European Space Agency]] (ESA).<ref name="harvey-2003">{{cite book |first=Brian |last=Harvey |title=Europe's Space Programme: To Ariane and Beyond |year=2003 |publisher=Springer Science & Business Media |isbn=1-8523-3722-2 }}</ref>{{Reference page|pages=161-162}} Six years later, in December 1979, the arrival of a capable European [[expendable launch system]] was marked when the first [[Ariane 1]] launcher was successfully launched from the [[Guiana Space Centre]] (CSG) at [[Kourou]], [[French Guiana]].<ref name="harvey-2003" />{{Reference page|page=169}} The Ariane 1 soon became considered to be a capable and competitive launcher in comparison to rival platforms offered by the [[Soviet Union]] and the [[United States|United States of America]], and it was quickly followed by improved derivatives in the form of the [[Ariane 2]] and [[Ariane 3]]. By early 1986, the Ariane 1, along with the Ariane 2 and Ariane 3, had become the dominant launcher on the world market.<ref name="harvey-2003" />{{Reference page|page=172}} | ||
In January 1982, the ESA issued its authorisation for the development and construction of the Ariane 4; the development programme had the stated objective of increasing the usable payload by 90%.<ref name= "encyc aria"/> The Ariane 4 would be a considerably larger and more flexible launcher that the earlier members of its family, being intended to compete with the upper end of launchers worldwide. In comparison, while the Ariane 1 had a typical weight of {{convert|207|t|lb}} and could launch payloads of up to {{convert|1.7|t|lb}} into orbit; the larger Ariane 4 had a typical weight of {{convert|470|t|lb}} and could orbit payloads of up to {{convert|4.2|t|lb}}.<ref name="harvey-2003" />{{ | In January 1982, the ESA issued its authorisation for the development and construction of the Ariane 4; the development programme had the stated objective of increasing the usable payload by 90%.<ref name= "encyc aria"/> The Ariane 4 would be a considerably larger and more flexible launcher that the earlier members of its family, being intended to compete with the upper end of launchers worldwide. In comparison, while the Ariane 1 had a typical weight of {{convert|207|t|lb}} and could launch payloads of up to {{convert|1.7|t|lb}} into orbit; the larger Ariane 4 had a typical weight of {{convert|470|t|lb}} and could orbit payloads of up to {{convert|4.2|t|lb}}.<ref name="harvey-2003" />{{Reference page|page=178}} Work on the Ariane 4 was substantially eased via drawing heavily on both the technology and experiences gained from producing and operating the earlier members of the [[Ariane (rocket family)|Ariane rocket]]. The total development cost for the Ariane 4 was valued at 476 million [[European Currency Unit]]s (ECU) in 1986.<ref name="encyc aria">{{Cite web |editor-last=Wade |editor-first=Mark |title=Ariane |url=http://www.astronautix.com/a/ariane.html |url-status=live |archive-url=https://web.archive.org/web/20240207065823/http://www.astronautix.com/a/ariane.html |archive-date=7 February 2024 |access-date=13 June 2015 |website=Encyclopedia Astronautica }}</ref> | ||
Posed with the requirement to produce a rocket with substantially greater thrust, the design team considered various approaches to achieve this.<ref name="harvey-2003" />{{ | Posed with the requirement to produce a rocket with substantially greater thrust, the design team considered various approaches to achieve this.<ref name="harvey-2003" />{{Reference page|page=179}} One concept studied had involved the addition of a fifth engine to an enlarged first stage of the Ariane 3, but was found to involve a very high level of redesign work to achieve this; instead, the first stage was elongated to hold {{convert|210|t|lb}} of propellant instead of the {{convert|145|t|lb}} present on the Ariane 3. While the second and third stages remained identical to the Ariane 3, a range of [[Booster (rocketry)|strap-on booster]]s were developed to be applied to the type, designed to gradually increase the rocket's payload capacity.<ref name="harvey-2003" />{{Reference page|page=179}} Overall, the Ariane 4 was 15% smaller than the Ariane 3.<ref name="harvey-2003" />{{Reference page|page=180}} | ||
In effect, the Ariane 4 was an improved and developed derivative of the earlier Ariane 3, primarily differing through the application of various [[Solid rocket booster|solid]]-fuelled and [[liquid rocket booster|liquid]]-fuelled boosters, the latter being the only all-new design feature of the Ariane 4; at this point, the practice of using liquid boosters was uncommon, having only previously been used in the [[Chinese space program]].<ref name="harvey-2003" />{{ | In effect, the Ariane 4 was an improved and developed derivative of the earlier Ariane 3, primarily differing through the application of various [[Solid rocket booster|solid]]-fuelled and [[liquid rocket booster|liquid]]-fuelled boosters, the latter being the only all-new design feature of the Ariane 4; at this point, the practice of using liquid boosters was uncommon, having only previously been used in the [[Chinese space program]].<ref name="harvey-2003" />{{Reference page|page=179}} Another innovation of the Ariane 4 was the dual-launch SPELDA (Structure Porteuse Externe de Lancement Double Ariane) fairing.<ref name="harvey-2003" />{{Reference page|page=180}} This had the function of allowing a pair of satellites, one placed on top of the other; several different SPELDA nose fairings could be installed, including normal and extended models. The SPELDA was considerably lighter than its predecessor; the guidance system also used much more accurate [[ring laser gyroscope]]s.<ref name="harvey-2003" />{{Reference page|page=180}} According to aviation author Brian Harvey, the advances present in the design of the Ariane 4 represented a conservative and evolutionary, rather than revolutionary, philosophy.<ref name="harvey-2003" />{{Reference page|page=180}} | ||
=== Teaming and construction === | === Teaming and construction === | ||
As the Ariane 4 programme took shape, it gained the support of [[Belgium]], [[Denmark]], [[Spain]], [[Ireland]], [[Italy]], the [[Netherlands]], [[Germany]], the [[United Kingdom]], [[France]], [[Sweden]], and [[Switzerland]].<ref name="harvey-2003" />{{ | As the Ariane 4 programme took shape, it gained the support of [[Belgium]], [[Denmark]], [[Spain]], [[Ireland]], [[Italy]], the [[Netherlands]], [[Germany]], the [[United Kingdom]], [[France]], [[Sweden]], and [[Switzerland]].<ref name="harvey-2003" />{{Reference page|page=180}} The main contractors were [[Aérospatiale]] (responsible for the first and second stages), [[Messerschmitt-Bölkow-Blohm]] (MBB) (produced the liquid-fuelled boosters), [[Safran Aircraft Engines|Société Européenne de Propulsion]] (SEP) (engine manufacturer), [[Matra]] (equipment bay assembly), [[Air Liquide]] (production of third stage tanks and insulation), [[Snia (company)|BPD Snia]] (maker of solid-fuelled boosters), and [[British Aerospace]]/[[RUAG|Contraves Space AG]] (manufacturers of the fairing).<ref name="harvey-2003" />{{Reference page|page=180}} For their work on the Ariane 4, the Launch Team were subsequently awarded the Space Achievement Award by the [[Space Foundation]] in 2004.<ref>{{Cite web |title=Awards |url=https://www.spacefoundation.org/what-we-do/awards/ |url-status=live |archive-url=https://web.archive.org/web/20240519040331/https://www.spacefoundation.org/what-we-do/awards/ |archive-date=19 May 2024 |access-date=13 June 2015 |publisher=[[Space Foundation]] }}</ref> | ||
In conjunction with the development of the Ariane 4 itself, a new purpose-built launch preparation area and launch pad for the rocket, collectively designated as ''ELA-2'', was constructed at the [[Guiana Space Centre|Centre Spatial Guyanais]] to service the Ariane 4 and provide a launch rate of 8 launches per year (this feat was near-unprecedented for a single large rocket, other than within the Soviet Union).<ref name="harvey-2003" />{{ | In conjunction with the development of the Ariane 4 itself, a new purpose-built launch preparation area and launch pad for the rocket, collectively designated as ''ELA-2'', was constructed at the [[Guiana Space Centre|Centre Spatial Guyanais]] to service the Ariane 4 and provide a launch rate of 8 launches per year (this feat was near-unprecedented for a single large rocket, other than within the Soviet Union).<ref name="harvey-2003" />{{Reference page|pages=178-179}} Unlike the earlier ''ELA-1'' which had been used for the previous members of the Ariane family and other rockets, preparation activity for the rocket would be performed in a purpose-built {{convert|80|m|ft|adj=on}} tall hall rather than on the pad itself; the completed rocket was then transported using a specially designed railway to slowly traverse from the hall to the launch pad, taking one hour. This railway provided the additional benefit of enabling faulty rockets to be withdrawn from the pad and be substituted for relatively quickly.<ref name="harvey-2003" />{{Reference page|page=179}} | ||
On 15 June 1988, the first successful launch of the Ariane 4 was conducted.<ref name="harvey-2003" />{{ | On 15 June 1988, the first successful launch of the Ariane 4 was conducted.<ref name="harvey-2003" />{{Reference page|page=180}} For this first test flight, it was decided to fire the second most powerful version of the rocket, designated ''44LP'', equipped with four main engines, two solid boosters and two liquid boosters; it was also furnished with the multi-satellite SPELDA fairing. 50 seconds after take-off, the solid boosters would be expended and be detached in order to reduce the rocket's weight.<ref name="harvey-2003" />{{Reference page|page=180}} 143 seconds after take-off, the liquid boosters also detached, further lightening the vehicle. The maiden flight was considered a success, putting multiple satellites into orbit.<ref name="harvey-2003" />{{Reference page|page=180}} | ||
=== Further development === | === Further development === | ||
For the V50 launch onwards, an improved third stage, known as the ''H10+'', was adopted for the Ariane 4.<ref name="harvey-2003" />{{ | For the V50 launch onwards, an improved third stage, known as the ''H10+'', was adopted for the Ariane 4.<ref name="harvey-2003" />{{Reference page|page=183}} The H10+ third stage featured a new tank, which was {{cvt|26|kg|lb}} lighter, {{cvt|32|cm|in}} longer, and contained {{cvt|340|kg|lb}} more fuel, which raised the rocket's overall payload capacity by {{cvt|110|kg|lb}} and increased its burn time by 20 seconds.<ref name="harvey-2003" />{{Reference page|page=183}} | ||
Even prior to the first flight of the Ariane 4, development of a successor, designated as the [[Ariane 5]], had already commenced.<ref name="harvey-2003" />{{ | Even prior to the first flight of the Ariane 4, development of a successor, designated as the [[Ariane 5]], had already commenced.<ref name="harvey-2003" />{{Reference page|pages=184-185}} In January 1985, the Ariane 5 had been officially adopted as an ESA programme. It lacked the high levels of commonality that the Ariane 4 had with its predecessors, and had been designed not only for launching heavier payloads of up to {{convert|5.2|t|lb}} and at a 20% cost reduction over the Ariane 4, but for a higher margin of safety due to the fact that the Ariane 5 was designed to conduct crewed space launches as well, being intended to transport [[astronaut]]s using the proposed [[Hermes (spacecraft)|Hermes space vehicle]].<ref name="harvey-2003" />{{Reference page|page=185}} Development of the Ariane 5 was not without controversy as some ESA members considered the more mature Ariane 4 to be more suited for meeting established needs for such launchers; it was for this reason that Britain chose not to participate in the Ariane 5 programme.<ref name="harvey-2003" />{{Reference page|page=186}} For some years, Ariane 4 and Ariane 5 launchers were operated interchangeably; however, it was eventually decided to terminate all Ariane 4 operations in favour of concentrating on the newer Ariane 5.<ref name="harvey-2003" />{{Reference page|page=193}} | ||
== Design == | == Design == | ||
The Ariane 4 was the ultimate development from the preceding members of the [[Ariane (rocket family)|Ariane rocket family]]. Compared with the [[Ariane 2]] and [[Ariane 3]], the Ariane 4 featured a stretched first (by 61%) and third stages, a strengthened structure, new propulsion bay layouts, new avionics, and the SPELDA ( | [[File:Ariane4.gif|thumb|upright=2.0|From left to right: Ariane 44LP, 40, 42P, 44P and 42L]]The Ariane 4 was the ultimate development from the preceding members of the [[Ariane (rocket family)|Ariane rocket family]]. Compared with the [[Ariane 2]] and [[Ariane 3]], the Ariane 4 featured a stretched first (by 61%) and third stages, a strengthened structure, new propulsion bay layouts, new avionics, and the SPELDA ({{Langx|fr|Structure Porteuse Externe de Lancement Double Ariane|4=External Carrying Structure for Ariane Double Launches}}), a satellite payload carrier system for launching more than one satellite at a time. | ||
The basic 40 version did not employ any strap-on motors, while the Ariane 42L, 44L, 42P, 44P, and 44LP variants all used various combinations of [[solid rocket booster|solid]] and [[Liquid rocket booster|liquid]] [[Booster (rocketry)|boosters]]. Originally designed to place {{cvt|2000|to|4200|kg|lb}} payloads in [[geostationary orbit]], the six Ariane 4 variants, aided by strap-on boosters, enabled the launch of payloads in excess of {{cvt|4900|kg|lb}} on several occasions. The Ariane 4 launcher reduced the launch costs per kilo by 55% in comparison to the original [[Ariane 1]].<ref name="harvey-2003" />{{Reference page|page=180}} | |||
The rocket was used in a number of variants | The rocket was used in a number of variants – it could be fitted with two or four additional boosters rockets: solid-fueled PAP ({{Langx|fr|Propulseurs d'Appoint à Poudre|4=Powder Booster Propellers|links=no}}) or liquid-fueled PAL ({{Langx|fr|Propulseurs d'Appoint à Liquide|4=Liquid Booster Propellers|links=no}}). | ||
The | The rocket captured nearly 60% of the world's commercial launch services market, serving both European and international clients.<ref>{{Cite web |date=9 June 2015 |title=Ariane 4, un défi pour l'Europe spatiale |trans-title=Ariane 4 - A challenge for Europe's space industry |url=https://ariane.cnes.fr/fr/web/CNES-fr/308-ariane-4-un-defi.php |url-status=live |archive-url=https://web.archive.org/web/20230923063802/https://ariane.cnes.fr/fr/web/CNES-fr/308-ariane-4-un-defi.php |archive-date=23 September 2023 |access-date=13 June 2015 |publisher=[[CNES]] |language=fr }}</ref> Atop the third stage was a vehicle equipment stage which housed a computer that performed various functions, including sequencing, guidance, control, tracking, [[telemetry]] and an explosive-based self-destruct.<ref name="harvey-2003" />{{Reference page|page=180}} | ||
[[ | The Ariane 4 AR 40 was the basic version, with three stages: {{cvt|58.4|m|ft}} high, a diameter of {{cvt|3.8|m|ft}}, a liftoff mass of {{cvt|245000|kg|lb}} and a maximum payload of {{cvt|2100|kg|lb}} to GTO or {{cvt|5000|kg|lb}} to [[low Earth orbit]] (LEO). Main power was provided by four [[Viking (rocket engine)|Viking 2B motors]], each producing {{cvt|667|kN|lbf}} of thrust. The second stage was powered by a single Viking 4B motor, and the third stage was equipped with an [[HM7B|HM7-B]] liquid oxygen/liquid hydrogen motor. The Ariane 4 AR 44L, which was outfitted with the maximum additional boost of four liquid fuel rocket strap-ons, was a four-stage rocket, weighing {{cvt|470000|kg|lb}} and capable of transferring a payload of {{cvt|4730|kg|lb}} to GTO, or alternatively {{cvt|7600|kg|lb}} to LEO. | ||
{| class="wikitable" style="margin:1em auto 1em auto; text-align:center;" | {| class="wikitable" style="margin:1em auto 1em auto; text-align:center;" | ||
| Line 151: | Line 138: | ||
! PAL | ! PAL | ||
! PAP | ! PAP | ||
! Payload to [[Geostationary transfer orbit|GTO]] | ! Payload to [[Geostationary transfer orbit|GTO]] | ||
! Launches | ! Launches | ||
! Successes | ! Successes | ||
! | !Failures | ||
!First flight | |||
!Last flight | |||
|----- | |----- | ||
| style="text-align:left;" | | | style="text-align:left;" | 40 | ||
| 0 || 0 || 2100 || 7 || 7 | | 0 || 0 || {{Convert|2100|kg|4=0|abbr=on}}|| 7 || 7 | ||
| | |0 | ||
|22 January 1990 | |||
|3 December 1999 | |||
|----- | |----- | ||
| style="text-align:left;" | | | style="text-align:left;" | 42P | ||
| 0 || 2 || 2930 || 15 || 14 | | 0 || 2 || {{Convert|2930|kg|4=0|abbr=on}}|| 15 || 14 | ||
| 1 | |1 | ||
|20 November 1990 | |||
|4 May 2002 | |||
|----- | |----- | ||
| style="text-align:left;" | | | style="text-align:left;" | 42L | ||
| 2 || 0 || 3480 || 13 || 13 | | 2 || 0 || {{Convert|3480|kg|4=0|abbr=on}}|| 13 || 13 | ||
| | |0 | ||
|12 May 1993 | |||
|23 January 2002 | |||
|----- | |----- | ||
| style="text-align:left;" | | | style="text-align:left;" | 44P | ||
| 0 || 4 || 3460 || 15 || 15 | | 0 || 4 || {{Convert|3460|kg|4=0|abbr=on}}|| 15 || 15 | ||
| | |0 | ||
|4 April 1991 | |||
|25 September 2001 | |||
|----- | |----- | ||
| style="text-align:left;" | | | style="text-align:left;" | 44LP | ||
| 2 || 2 || 4220 || 26 || 25 | | 2 || 2 || {{Convert|4220|kg|4=0|abbr=on}}|| 26 || 25 | ||
| | |1 | ||
|15 June 1988 | |||
|27 November 2001 | |||
|----- | |----- | ||
| style="text-align:left;" | | | style="text-align:left;" | 44L | ||
| 4 || 0 || 4720 || 40 || 39 | | 4 || 0 || {{Convert|4720|kg|4=0|abbr=on}}|| 40 || 39 | ||
| | |1 | ||
|5 June 1989 | |||
|15 February 2003 | |||
|} | |} | ||
| Line 186: | Line 187: | ||
In June 1988, the inaugural flight of the Ariane 4 occurred, which was a success. Since then, Ariane 4 has flown 116 times, 113 of which were successful, yielding a success rate of {{percent|113|116|1}}. | In June 1988, the inaugural flight of the Ariane 4 occurred, which was a success. Since then, Ariane 4 has flown 116 times, 113 of which were successful, yielding a success rate of {{percent|113|116|1}}. | ||
On 22 February 1990, the first failure occurred during the eighth Ariane 4 launch, flight V36. The rocket exploded 9 km above Kourou.<ref name="harvey-2003" />{{ | On 22 February 1990, the first failure occurred during the eighth Ariane 4 launch, flight V36. The rocket exploded 9 km above Kourou.<ref name="harvey-2003" />{{Reference page|pages=182-183}} The failure occurred because a worker assembling a [[Viking (rocket engine)|Viking rocket motor]] had left a handkerchief in one of the motor's coolant tubes. He had done so as a reminder to himself to inform his superior, as per procedure, of an unplanned polishing he had made to fit the tube. But he fell ill before he could do so and was replaced by other workers who did not notice the handkerchief. In flight, the handkerchief blocked the coolant tube, the motor overheated and failed, and the Ariane self-destructed after veering off its trajectory. Its payload, two communications satellites worth 500 million US dollars ([[Superbird-B]] and [[Yuri (satellite)|BS-2X]]) landed in pieces in the swamps near Kourou.<ref name="Castanos-2020">{{Cite web |last=Castanos |first=Francis |date=7 December 2020 |title=The Space Review: The cloth of doom: The weird, doomed ride of Ariane Flight 36 |url=https://www.thespacereview.com/article/4085/1 |url-status=live |archive-url=https://web.archive.org/web/20231204195450/https://thespacereview.com/article/4085/1 |archive-date=4 December 2023 |access-date=10 December 2020 |website=[[The Space Review]]}}</ref> The ensuing investigation recommended 44 modifications, including numbering and checking all pieces of cloth used in the rocket's assembly.<ref name="Castanos-2020" /> The following 26 launches were all completed successfully.<ref name="harvey-2003" />{{Reference page|page=183}} | ||
The system became the basis for European [[satellite]] launches with a record of 113 successful and three launch failures. Ariane 4 provided a payload increase from {{cvt|1700|kg|lb}} for [[Ariane 3]] to a maximum of {{cvt|4800|kg|lb}} to [[geostationary transfer orbit]] (GTO). The record for Ariane 4 to GTO was {{cvt|4946|kg|lb}}.<ref>{{cite web|url=http://www.space-airbusds.com/en/programmes/ariane-4.html|title=Ariane 4|publisher=Airbus Defence and Space|access-date=13 June 2015|archive-date=27 September 2016|archive-url=https://web.archive.org/web/20160927235322/http://www.space-airbusds.com/en/programmes/ariane-4.html|url-status=dead}}</ref> | The system became the basis for European [[satellite]] launches with a record of 113 successful and three launch failures. Ariane 4 provided a payload increase from {{cvt|1700|kg|lb}} for [[Ariane 3]] to a maximum of {{cvt|4800|kg|lb}} to [[geostationary transfer orbit]] (GTO). The record for Ariane 4 to GTO was {{cvt|4946|kg|lb}}.<ref>{{cite web|url=http://www.space-airbusds.com/en/programmes/ariane-4.html|title=Ariane 4|publisher=Airbus Defence and Space|access-date=13 June 2015|archive-date=27 September 2016|archive-url=https://web.archive.org/web/20160927235322/http://www.space-airbusds.com/en/programmes/ariane-4.html|url-status=dead}}</ref> | ||
On 15 February 2003, the final launch of Ariane 4 rocket occurred, placing [[Intelsat 907]] into [[geosynchronous orbit]].<ref name="arianespace-20030215">{{Cite press release |date=15 February 2003 |title=Arianespace Flight 159: Mission Accomplished! 23rd launch for Intelsat |url=https://www.arianespace.com/press-release/arianespace-flight-159-mission-accomplished-23rd-launch-for-intelsat/ |url-status=live |archive-url=https://web.archive.org/web/20230706025156/https://www.arianespace.com/press-release/arianespace-flight-159-mission-accomplished-23rd-launch-for-intelsat/ |archive-date=6 July 2023 |access-date=28 May 2024 |publisher=[[Arianespace]] }}</ref> Arianespace had decided to phase out the Ariane 4 launcher in favour of the newer heavy-lift [[Ariane 5]] rocket, which had already been in service for some years. In 2011, the medium-lift [[Soyuz-2|Soyuz ST]] complemented the offering of launch vehicles from the [[ | On 15 February 2003, the final launch of Ariane 4 rocket occurred, placing [[Intelsat 907]] into [[geosynchronous orbit]].<ref name="arianespace-20030215">{{Cite press release |date=15 February 2003 |title=Arianespace Flight 159: Mission Accomplished! 23rd launch for Intelsat |url=https://www.arianespace.com/press-release/arianespace-flight-159-mission-accomplished-23rd-launch-for-intelsat/ |url-status=live |archive-url=https://web.archive.org/web/20230706025156/https://www.arianespace.com/press-release/arianespace-flight-159-mission-accomplished-23rd-launch-for-intelsat/ |archive-date=6 July 2023 |access-date=28 May 2024 |publisher=[[Arianespace]] }}</ref> Arianespace had decided to phase out the Ariane 4 launcher in favour of the newer heavy-lift [[Ariane 5]] rocket, which had already been in service for some years. In 2011, the medium-lift [[Soyuz-2|Soyuz ST]] complemented the offering of launch vehicles from the [[Guiana Space Centre]]. Spacecraft launched by the Soyuz reused the payload platform and dispenser which had been originally designed for the Ariane.<ref>{{Cite web |date=March 2012 |title=Soyuz User's Manual |url=http://www.arianespace.com/launch-services-soyuz/Soyuz-Users-Manual-March-2012.pdf |url-status=dead |archive-url=https://web.archive.org/web/20131228235729/http://www.arianespace.com/launch-services-soyuz/Soyuz-Users-Manual-March-2012.pdf |archive-date=28 December 2013 |access-date=13 June 2015 |publisher=[[Arianespace]] }}</ref> | ||
== Comparable rockets == | == Comparable rockets == | ||
* [[Delta II]] (retired) | * [[Delta II]] (retired) | ||
* [[ | * [[Geosynchronous Satellite Launch Vehicle|GSLV Mk II]] | ||
* [[GSLV Mk III]] | * [[LVM3|GSLV Mk III]] | ||
* [[Long March 3B]] | * [[Long March 3B]] | ||
* [[Soyuz-U]] (retired) | * [[Soyuz-U]] (retired) | ||
| Line 201: | Line 202: | ||
== See also == | == See also == | ||
{{Portal|Spaceflight}} | {{Portal|Spaceflight}} | ||
* [[Comparison of orbital | * [[Comparison of orbital launcher families]] | ||
* [[Tsyklon-4]] (Ukrainian carrier rocket with fairing derived from Ariane 4) | * [[Tsyklon-4]] (Ukrainian carrier rocket with fairing derived from Ariane 4) | ||
Latest revision as of 21:07, 17 November 2025
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The Ariane 4 was a European expendable launch vehicle in the Ariane family, developed by the Script error: No such module "Lang". (CNES), the French space agency, for the European Space Agency (ESA). The manufacturing of the launch vehicle was led by Aérospatiale and it was marketed by Arianespace. Since its first flight on 15 June 1988 until the final flight on 15 February 2003, it attained 113 successful launches out of 116 total launches.
In 1982, the Ariane 4 program was approved by ESA. Drawing heavily upon the preceding Ariane 3, it was designed to provide a launcher capable of delivering heavier payloads and at a lower cost per kilogram than the earlier members of the Ariane family. The Ariane 4 was principally an evolution of the existing technologies used, as opposed to being revolutionary in its design ethos; this approach quickly gained the backing of most ESA members, who funded and participated in its development and operation. Capable of being equipped with a wide variety of strap-on boosters, the Ariane 4 gained a reputation for being an extremely versatile launcher.
Once in service, the launcher soon became recognized for being ideal for launching communications and Earth observation satellites, as well as those used for scientific research. During its working life, the Ariane 4 managed to capture 50% of the market in launching commercial satellites, soundly demonstrating Europe's ability to compete in the commercial launch sector.[1] In February 2003, the final Ariane 4 was launched; Arianespace had decided to retire the type in favour of the newer and larger Ariane 5, which effectively replaced it in service.
Development
Origins
In 1973, eleven nations decided to pursue joint collaboration in the field of space exploration and formed a new pan-national organisation to undertake this mission, the European Space Agency (ESA).[2]Template:Reference page Six years later, in December 1979, the arrival of a capable European expendable launch system was marked when the first Ariane 1 launcher was successfully launched from the Guiana Space Centre (CSG) at Kourou, French Guiana.[2]Template:Reference page The Ariane 1 soon became considered to be a capable and competitive launcher in comparison to rival platforms offered by the Soviet Union and the United States of America, and it was quickly followed by improved derivatives in the form of the Ariane 2 and Ariane 3. By early 1986, the Ariane 1, along with the Ariane 2 and Ariane 3, had become the dominant launcher on the world market.[2]Template:Reference page
In January 1982, the ESA issued its authorisation for the development and construction of the Ariane 4; the development programme had the stated objective of increasing the usable payload by 90%.[3] The Ariane 4 would be a considerably larger and more flexible launcher that the earlier members of its family, being intended to compete with the upper end of launchers worldwide. In comparison, while the Ariane 1 had a typical weight of Template:Convert and could launch payloads of up to Template:Convert into orbit; the larger Ariane 4 had a typical weight of Template:Convert and could orbit payloads of up to Template:Convert.[2]Template:Reference page Work on the Ariane 4 was substantially eased via drawing heavily on both the technology and experiences gained from producing and operating the earlier members of the Ariane rocket. The total development cost for the Ariane 4 was valued at 476 million European Currency Units (ECU) in 1986.[3]
Posed with the requirement to produce a rocket with substantially greater thrust, the design team considered various approaches to achieve this.[2]Template:Reference page One concept studied had involved the addition of a fifth engine to an enlarged first stage of the Ariane 3, but was found to involve a very high level of redesign work to achieve this; instead, the first stage was elongated to hold Template:Convert of propellant instead of the Template:Convert present on the Ariane 3. While the second and third stages remained identical to the Ariane 3, a range of strap-on boosters were developed to be applied to the type, designed to gradually increase the rocket's payload capacity.[2]Template:Reference page Overall, the Ariane 4 was 15% smaller than the Ariane 3.[2]Template:Reference page
In effect, the Ariane 4 was an improved and developed derivative of the earlier Ariane 3, primarily differing through the application of various solid-fuelled and liquid-fuelled boosters, the latter being the only all-new design feature of the Ariane 4; at this point, the practice of using liquid boosters was uncommon, having only previously been used in the Chinese space program.[2]Template:Reference page Another innovation of the Ariane 4 was the dual-launch SPELDA (Structure Porteuse Externe de Lancement Double Ariane) fairing.[2]Template:Reference page This had the function of allowing a pair of satellites, one placed on top of the other; several different SPELDA nose fairings could be installed, including normal and extended models. The SPELDA was considerably lighter than its predecessor; the guidance system also used much more accurate ring laser gyroscopes.[2]Template:Reference page According to aviation author Brian Harvey, the advances present in the design of the Ariane 4 represented a conservative and evolutionary, rather than revolutionary, philosophy.[2]Template:Reference page
Teaming and construction
As the Ariane 4 programme took shape, it gained the support of Belgium, Denmark, Spain, Ireland, Italy, the Netherlands, Germany, the United Kingdom, France, Sweden, and Switzerland.[2]Template:Reference page The main contractors were Aérospatiale (responsible for the first and second stages), Messerschmitt-Bölkow-Blohm (MBB) (produced the liquid-fuelled boosters), Société Européenne de Propulsion (SEP) (engine manufacturer), Matra (equipment bay assembly), Air Liquide (production of third stage tanks and insulation), BPD Snia (maker of solid-fuelled boosters), and British Aerospace/Contraves Space AG (manufacturers of the fairing).[2]Template:Reference page For their work on the Ariane 4, the Launch Team were subsequently awarded the Space Achievement Award by the Space Foundation in 2004.[4]
In conjunction with the development of the Ariane 4 itself, a new purpose-built launch preparation area and launch pad for the rocket, collectively designated as ELA-2, was constructed at the Centre Spatial Guyanais to service the Ariane 4 and provide a launch rate of 8 launches per year (this feat was near-unprecedented for a single large rocket, other than within the Soviet Union).[2]Template:Reference page Unlike the earlier ELA-1 which had been used for the previous members of the Ariane family and other rockets, preparation activity for the rocket would be performed in a purpose-built Template:Convert tall hall rather than on the pad itself; the completed rocket was then transported using a specially designed railway to slowly traverse from the hall to the launch pad, taking one hour. This railway provided the additional benefit of enabling faulty rockets to be withdrawn from the pad and be substituted for relatively quickly.[2]Template:Reference page
On 15 June 1988, the first successful launch of the Ariane 4 was conducted.[2]Template:Reference page For this first test flight, it was decided to fire the second most powerful version of the rocket, designated 44LP, equipped with four main engines, two solid boosters and two liquid boosters; it was also furnished with the multi-satellite SPELDA fairing. 50 seconds after take-off, the solid boosters would be expended and be detached in order to reduce the rocket's weight.[2]Template:Reference page 143 seconds after take-off, the liquid boosters also detached, further lightening the vehicle. The maiden flight was considered a success, putting multiple satellites into orbit.[2]Template:Reference page
Further development
For the V50 launch onwards, an improved third stage, known as the H10+, was adopted for the Ariane 4.[2]Template:Reference page The H10+ third stage featured a new tank, which was Template:Cvt lighter, Template:Cvt longer, and contained Template:Cvt more fuel, which raised the rocket's overall payload capacity by Template:Cvt and increased its burn time by 20 seconds.[2]Template:Reference page
Even prior to the first flight of the Ariane 4, development of a successor, designated as the Ariane 5, had already commenced.[2]Template:Reference page In January 1985, the Ariane 5 had been officially adopted as an ESA programme. It lacked the high levels of commonality that the Ariane 4 had with its predecessors, and had been designed not only for launching heavier payloads of up to Template:Convert and at a 20% cost reduction over the Ariane 4, but for a higher margin of safety due to the fact that the Ariane 5 was designed to conduct crewed space launches as well, being intended to transport astronauts using the proposed Hermes space vehicle.[2]Template:Reference page Development of the Ariane 5 was not without controversy as some ESA members considered the more mature Ariane 4 to be more suited for meeting established needs for such launchers; it was for this reason that Britain chose not to participate in the Ariane 5 programme.[2]Template:Reference page For some years, Ariane 4 and Ariane 5 launchers were operated interchangeably; however, it was eventually decided to terminate all Ariane 4 operations in favour of concentrating on the newer Ariane 5.[2]Template:Reference page
Design
The Ariane 4 was the ultimate development from the preceding members of the Ariane rocket family. Compared with the Ariane 2 and Ariane 3, the Ariane 4 featured a stretched first (by 61%) and third stages, a strengthened structure, new propulsion bay layouts, new avionics, and the SPELDA (Template:Langx), a satellite payload carrier system for launching more than one satellite at a time.
The basic 40 version did not employ any strap-on motors, while the Ariane 42L, 44L, 42P, 44P, and 44LP variants all used various combinations of solid and liquid boosters. Originally designed to place Template:Cvt payloads in geostationary orbit, the six Ariane 4 variants, aided by strap-on boosters, enabled the launch of payloads in excess of Template:Cvt on several occasions. The Ariane 4 launcher reduced the launch costs per kilo by 55% in comparison to the original Ariane 1.[2]Template:Reference page
The rocket was used in a number of variants – it could be fitted with two or four additional boosters rockets: solid-fueled PAP (Template:Langx) or liquid-fueled PAL (Template:Langx).
The rocket captured nearly 60% of the world's commercial launch services market, serving both European and international clients.[5] Atop the third stage was a vehicle equipment stage which housed a computer that performed various functions, including sequencing, guidance, control, tracking, telemetry and an explosive-based self-destruct.[2]Template:Reference page
The Ariane 4 AR 40 was the basic version, with three stages: Template:Cvt high, a diameter of Template:Cvt, a liftoff mass of Template:Cvt and a maximum payload of Template:Cvt to GTO or Template:Cvt to low Earth orbit (LEO). Main power was provided by four Viking 2B motors, each producing Template:Cvt of thrust. The second stage was powered by a single Viking 4B motor, and the third stage was equipped with an HM7-B liquid oxygen/liquid hydrogen motor. The Ariane 4 AR 44L, which was outfitted with the maximum additional boost of four liquid fuel rocket strap-ons, was a four-stage rocket, weighing Template:Cvt and capable of transferring a payload of Template:Cvt to GTO, or alternatively Template:Cvt to LEO.
| Model | PAL | PAP | Payload to GTO | Launches | Successes | Failures | First flight | Last flight |
|---|---|---|---|---|---|---|---|---|
| 40 | 0 | 0 | Template:Convert | 7 | 7 | 0 | 22 January 1990 | 3 December 1999 |
| 42P | 0 | 2 | Template:Convert | 15 | 14 | 1 | 20 November 1990 | 4 May 2002 |
| 42L | 2 | 0 | Template:Convert | 13 | 13 | 0 | 12 May 1993 | 23 January 2002 |
| 44P | 0 | 4 | Template:Convert | 15 | 15 | 0 | 4 April 1991 | 25 September 2001 |
| 44LP | 2 | 2 | Template:Convert | 26 | 25 | 1 | 15 June 1988 | 27 November 2001 |
| 44L | 4 | 0 | Template:Convert | 40 | 39 | 1 | 5 June 1989 | 15 February 2003 |
Operational history
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In June 1988, the inaugural flight of the Ariane 4 occurred, which was a success. Since then, Ariane 4 has flown 116 times, 113 of which were successful, yielding a success rate of Script error: No such module "Percentage"..
On 22 February 1990, the first failure occurred during the eighth Ariane 4 launch, flight V36. The rocket exploded 9 km above Kourou.[2]Template:Reference page The failure occurred because a worker assembling a Viking rocket motor had left a handkerchief in one of the motor's coolant tubes. He had done so as a reminder to himself to inform his superior, as per procedure, of an unplanned polishing he had made to fit the tube. But he fell ill before he could do so and was replaced by other workers who did not notice the handkerchief. In flight, the handkerchief blocked the coolant tube, the motor overheated and failed, and the Ariane self-destructed after veering off its trajectory. Its payload, two communications satellites worth 500 million US dollars (Superbird-B and BS-2X) landed in pieces in the swamps near Kourou.[6] The ensuing investigation recommended 44 modifications, including numbering and checking all pieces of cloth used in the rocket's assembly.[6] The following 26 launches were all completed successfully.[2]Template:Reference page
The system became the basis for European satellite launches with a record of 113 successful and three launch failures. Ariane 4 provided a payload increase from Template:Cvt for Ariane 3 to a maximum of Template:Cvt to geostationary transfer orbit (GTO). The record for Ariane 4 to GTO was Template:Cvt.[7]
On 15 February 2003, the final launch of Ariane 4 rocket occurred, placing Intelsat 907 into geosynchronous orbit.[8] Arianespace had decided to phase out the Ariane 4 launcher in favour of the newer heavy-lift Ariane 5 rocket, which had already been in service for some years. In 2011, the medium-lift Soyuz ST complemented the offering of launch vehicles from the Guiana Space Centre. Spacecraft launched by the Soyuz reused the payload platform and dispenser which had been originally designed for the Ariane.[9]
Comparable rockets
- Delta II (retired)
- GSLV Mk II
- GSLV Mk III
- Long March 3B
- Soyuz-U (retired)
See also
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- Comparison of orbital launcher families
- Tsyklon-4 (Ukrainian carrier rocket with fairing derived from Ariane 4)
References
External links
Template:Ariane Template:Expendable launch systems Template:European launch systems
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