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'{{short description|Russian heavy lift launcher, hypergolic fuel}} {{Use British English|date=August 2020}} {{Use dmy dates|date=August 2020}} {{Infobox rocket |image = On the launch pad.jpg |caption = Proton-M rocket on the launchpad at [[Baikonur Cosmodrome]] |manufacturer = [[Khrunichev State Research and Production Space Center|Khrunichev]] |function = [[Heavy-lift launch vehicle]] |country-origin = [[Russia]] |cpl = US$65 million<ref name=gao-surplus>{{cite report|url=https://www.gao.gov/assets/690/686613.pdf|title=Surplus Missile Motors|id=GAO-17-609|publisher=United States Government Accountability Office|date=August 2017|access-date=27 November 2018}} {{PD-notice}}</ref> |mass = {{cvt|705000|kg}}<ref name="ils-lv">{{cite web|url=http://www.ilslaunch.com/launch-services/ils-proton-breeze-m-launch-vehicle|title=Commercial Launch Vehicle {{!}} ILS Proton Breeze M |publisher=[[International Launch Services]]|access-date=2016-04-07}}</ref> |height = {{cvt|58.2|m}} |diameter = {{cvt|7.4|m}} |stages = 3 or 4 |capacities = {{Infobox rocket/Payload |location = [[Low Earth orbit|LEO]]{{efn|{{cvt|180|km}} circular LEO 51.5° [[Orbital inclination|inclination]] from [[Baikonur Cosmodrome|Baikonur]]}} |kilos = {{cvt|23000|kg}}<ref name="proton-performance">{{cite web|title=Proton Launch System Mission Planner's Guide – Section 2. LV Performance |url=http://www.ilslaunch.com/sites/default/files/pdf/PMPG%20Section%202.pdf|publisher=[[International Launch Services]]|date=July 2009|access-date=June 11, 2017}}</ref> }} {{Infobox rocket/Payload |location = [[Geostationary transfer orbit|GTO]] (1800 m/s) |kilos = {{cvt|6920|kg}}<ref name=proton-performance/> }} {{Infobox rocket/Payload |location = [[Geostationary transfer orbit|GTO]] (1500 m/s) |kilos = {{cvt|6300|kg}}<ref>{{cite web|date=June 9, 2016|publisher=Spaceflightnow.com|url=http://spaceflightnow.com/2016/06/09/upgraded-proton-booster-adds-satellite-to-intelsats-fleet/ |last=Clark|first=Stephen|title=Upgraded Proton booster adds satellite to Intelsat's fleet}}</ref> }} {{Infobox rocket/Payload |location = [[Geostationary orbit|GSO]] |kilos = {{cvt|3250|kg}}<ref name=proton-performance /> }} |family = [[Universal Rocket]] | comparable = {{flatlist| * [[Ariane 5]] * [[Atlas V|Atlas V 551]] * [[Delta IV Heavy]] * [[Falcon 9 FT]] * [[H-IIB]] * [[Long March 5]] }} |status = Active |sites = {{plainlist| * [[Baikonur Cosmodrome|Baikonur]], [[Baikonur Cosmodrome Site 81|Site 81/24]] * [[Baikonur Cosmodrome|Baikonur]], [[Baikonur Cosmodrome Site 200|Site 200/39]] }} |launches = 111 <!-- The counts of total launches (108), failed launches (9), partial failures (2) and successful launches (97) are up to date as of 30 July 2020 at 21:25:19 UTC and correspond exactly to the Wikipedia article: List of Proton launches, as that article was on 30 July 2020 at 21:25:19 UTC. DO NOT CHANGE COUNTS HERE UNLESS YOU ALSO MAKE CHANGES TO THE ARTICLE: LIST OF PROTON LAUNCHES--> |fail = 9 <!-- 5 FTO (2 x GLONASS, JCSAT-11, Ekspress-AM4R, MexSat-1), plus Arabsat-4A, Ekspress-AM4 and Ekspress-MD2/Telkom in unusable/unrecoverable orbits; AMC-14 unusable but salvaged by new owner on a different mission, still counts as a failed launch --> |partial = 2 <!-- Yamal 402 and Ekspress-AM6 managed to reach its intended orbit under its own power --> |success = 100 |first = 7 April 2001<ref>{{cite web|url=http://planet4589.org/space/lvdb/launch/Proton|title=Proton|work=Orbital and Suborbital Launch Database|first=Jonathan|last=McDowell|publisher=Jonathan's Space Page}}</ref> |last = 21 July 2021 |payloads = [[GLONASS]], [[ExoMars]]<!-- Notable payloads --> <!--Stages/boosters (optional)--> |stagedata = {{Infobox Rocket/Stage |type = stage |stageno = First |engines = 6 [[RD-253|RD-275M]] |name = 8S810K |thrust = {{cvt|10532|kN}} |SI = 285 seconds |burntime = 108 seconds |fuel = [[Dinitrogen tetroxide|N₂O₄]] / [[Unsymmetrical dimethylhydrazine|UDMH]] |length = {{cvt|21.18|m}}<ref name="ils-1st-2nd">{{cite web|url=http://www.ilslaunch.com/launch-services/ils-proton-breeze-m-launch-vehicle/proton-1st-2nd-stage|title=1st and 2nd Stage {{!}} ILS Proton {{!}} Launch Vehicle|publisher=[[International Launch Services]]|access-date=2016-04-07}}</ref> |diameter = {{cvt|7.4|m}} |propmass = {{cvt|428300|kg}} |empty = {{cvt|30600|kg}} }} {{Infobox Rocket/Stage |type = stage |stageno = Second |engines = 3 [[RD-0210]] 1 [[RD-0211]] |name = 8S811K |thrust = {{cvt|2399|kN}} |SI = 327 seconds |burntime = 206 seconds |fuel = N₂O₄ / UDMH |length = {{cvt|17.05|m}}<ref name="ils-1st-2nd"/> |diameter = {{cvt|4.1|m}} |propmass = {{cvt|157300|kg}} |empty = {{cvt|11000|kg}} }} {{Infobox Rocket/Stage |type = stage |stageno = Third |engines = 1 [[RD-0212]] |name = 8S812 |thrust = {{cvt|613.8|kN}} |SI = 325 seconds |burntime = 238 seconds |fuel = N₂O₄ / UDMH |length = {{cvt|4.11|m}}<ref name="ils-3rd">{{cite web|url=http://www.ilslaunch.com/launch-services/ils-proton-breeze-m-launch-vehicle/3rd-stage|title=3rd Stage {{!}} ILS Proton {{!}} Launch Vehicle |publisher=[[International Launch Services]]|access-date=2016-04-07}}</ref> |diameter = {{cvt|4.1|m}} |propmass = {{cvt|46562|kg}} |empty = {{cvt|3500|kg}} }} {{Infobox Rocket/Stage |type = stage |stageno = Fourth |diff = optional |name = [[Briz (rocket stage)|Briz-M]] |engines = 1 [[S5.98M]] |thrust = {{cvt|19.62|kN}}<ref name="ils-brizm">{{cite web|url=http://www.ilslaunch.com/launch-services/ils-proton-breeze-m-launch-vehicle/breeze-m|title=Breeze M {{!}} ILS Proton {{!}} Launch Vehicle |publisher=[[International Launch Services]]|access-date=2016-04-07}}</ref> |SI = 326 seconds |burntime = 3000 seconds |fuel = N₂O₄ / UDMH |length = {{cvt|2.61|m}} |diameter = {{cvt|4.0|m}} |propmass = {{cvt|19800|kg}} |empty = {{cvt|2370|kg}} }} {{Infobox Rocket/Stage |type = stage |stageno = Fourth |diff = optional |name = [[Blok D|Blok DM-2]] |engines = 1 [[RD-58M]] |thrust = {{cvt|85|kN}} |SI = 352 seconds |burntime = |fuel = [[RP-1]] / [[liquid oxygen|LOX]] }} {{Infobox Rocket/Stage |type = stage |stageno = Fourth |diff = optional |name = [[Blok DM-03]] |engines = 1 [[RD-58|RD-58M/RD-58MF]] |thrust = |SI = |burntime = |fuel = RP-1 / LOX }} }} The '''Proton-M''', (Протон-М) [[GRAU index]] '''8K82M''' or '''{{Not a typo|8K82KM}}''', is an expendable Russian [[heavy-lift launch vehicle]] derived from the [[Soviet Union|Soviet]]-developed [[Proton (rocket family)|Proton]]. It is built by [[Khrunichev State Research and Production Space Center|Khrunichev]], and launched from sites [[Baikonur Cosmodrome Site 81|81]] and [[Baikonur Cosmodrome Site 200|200]] at the [[Baikonur Cosmodrome]] in [[Kazakhstan]]. Commercial launches are marketed by [[International Launch Services]] (ILS), and generally use Site 200/39. The first Proton-M launch occurred on 7 April 2001.<ref>{{cite web|url=http://www.ilslaunch.com/launch-services/ils-proton-breeze-m-launch-vehicle/proton-heritage|title=Commercial Launch Heritage {{!}} Proton Rocket|publisher=[[International Launch Services]] |access-date=2016-04-10}}</ref> Proton flew its most recent mission on 30 July 2020, delivering [[Ekspress|Ekspress-80]] and [[Ekspress|Ekspress-103]] to geostationary orbit.<ref>http://russianspaceweb.com/eutelsat5wb-mev1.html</ref> As of August 2020, a number of [[Roscosmos]] and other Russian government missions remain on Proton launch manifest. == Vehicle description == {{stack|float=left|cellspacing=0|[[File:First stage Proton M cropped.jpg|left|thumb|Proton-M rollout]]}} The Proton-M launch vehicle consists of three stages; all of them powered by [[liquid rocket engine]]s using the [[hypergolic propellant]] combination of [[dinitrogen tetroxide]] as the oxidizer, and [[unsymmetrical dimethylhydrazine]] for fuel. The first stage is unique in that it consists of a central cylindrical oxidizer tank with the same diameter as the other two stages with six fuel tanks attached to its circumference, each carrying an engine. The engines in this stage can swivel tangentially up to 7.0° from the neutral position, providing full [[thrust vector control]]. The rationale for this design is logistics: the diameter of the oxidizer tanks and the two following stages is the maximum that can be delivered by railroad to Baikonur. However, within Baikonur the fully assembled stack is transported again by rail, as it has enough clearance. The second stage uses a conventional cylindrical design. It is powered by three [[RD-0210]] engines and one [[RD-0210|RD-0211]] engine. The RD-0211 is a modified version of the RD-0210 used to pressurize the propellant tanks. The second stage is joined to the first stage through a net instead of a closed inter-stage, to allow the exhaust to escape because the second stage begins firing seconds before separation. Thrust vector control is provided by engine gimballing. The third stage is also of a conventional cylindrical design. It contains the avionics system that controls the first two stages. It uses one [[RD-0210|RD-0213]] which is a fixed (non-gimballed) version of the RD-0210, and one [[RD-0214]] which is a four nozzle [[vernier engine]] used for thrust vector control. The nozzles of the RD-0214 can turn up to 45.0°; they are placed around (with some separation), and moderately above the nozzle of the RD-0213. The Proton-M features modifications to the lower stages to reduce structural mass, increase thrust, and utilise more propellant. A closed-loop guidance system is used on the first stage, which allows more complete consumption of propellant. This increases the rocket's performance slightly compared to previous variants, and reduces the amount of toxic chemicals remaining in the stage when it impacts downrange. It can place up to {{convert|21000|kg}} into [[low Earth orbit]]. With an upper stage, it can place a 3000&nbsp;kg payload into [[geostationary orbit]] (GEO), or a 5500&nbsp;kg payload into [[geostationary transfer orbit]] (GTO). Efforts were also made to reduce dependency on foreign component suppliers. === Upper stage === Most Proton-M launches have used a [[Briz (rocket stage)|Briz-M]] upper stage to propel the spacecraft into a higher orbit. Launches have also been made with [[Blok D|Blok-DM]] upper stages: six launches were made with the [[Blok D|Blok DM-02]] upper stage carrying [[GLONASS]] spacecraft, while two further GLONASS launches have used the [[Blok DM-03]].<ref>{{cite web |url=http://space.skyrocket.de/doc_lau_fam/proton.htm|title=Proton|first=Gunter|last=Krebs|publisher=Gunter's Space Page}}</ref> The DM-03 will be used for a total of five launches; a further GLONASS launch is planned along with two launches of [[Ekspress]] satellites. As of 2013, no Proton-M launches have been made without an upper stage. However, this configuration is manifested to launch the [[Nauka (ISS module)]] and [[European Robotic Arm]] (ERA) of the [[International Space Station]], currently scheduled to be launched together in July 2021. === Payload fairing === {{stack|float=right|cellspacing=0|[[File:Proton-M ILS fairings ver 1.jpg|left|thumb|Proton-M/Briz-M payload fairing]]}} Commercial launches conducted by ILS use two kinds of fairings:<ref>{{cite web|url=http://www.ilslaunch.com/launch-services/ils-proton-breeze-m-launch-vehicle/payload-fairing|title=Payload Fairing {{!}} ILS Proton {{!}} Launch Vehicle|publisher=[[International Launch Services]]|access-date=2016-04-07}}</ref><ref>{{cite web|title=Proton Launch System Mission Planner's Guide Section 4 Spacecraft Interfaces |url=http://www.ilslaunch.com/sites/default/files/pdf/PMPG%20Section%204.pdf|publisher=[[International Launch Services]]|access-date=2016-04-07}}</ref> *'''PLF-BR-13305''' short faring. *'''PLF-BR-15255''' long faring. Both fairings have a diameter of 4.35 metre. === Proton-M Enhanced (M+) === On 7 July 2007, [[International Launch Services]] launched the first '''Proton-M Enhanced''' rocket (also called '''M+'''), which carried the [[T10 (satellite)|DirecTV-10]] satellite into orbit. This was the 326th launch of a Proton, the 16th Proton-M/Briz-M launch, and the 41st Proton launch to be conducted by ILS.<ref>{{cite web|url=http://www.ilslaunch.com/mission-control/mission-directv-10|title=DIRECTV 10 |publisher=[[International Launch Services|ILS]]}}</ref> It features more efficient first stage engines, updated avionics, lighter fuel tanks and more powerful [[vernier thruster|vernier engines]] on the Briz-M upper stage, and [[mass]] reduction throughout the rocket, including thinner fuel tank walls on the first stage, and use of composite materials on all other stages. The second launch of this variant occurred on 18 August 2008, and was used to place [[Inmarsat|Inmarsat 4 F3]] into orbit. The baseline Proton-M was retired in November 2007, in favour of the Enhanced variant. Frank McKenna, CEO of ILS, has indicated that in 2010 the Phase III Proton design would become the standard ILS configuration, with the ability to lift 6150&nbsp;kg to GTO.<ref>{{cite web |url=http://www.ilslaunch.com/newsroom/ils-news/satellite-finance-article-ils-reaps-rewards-khrunichev-takeover|title=ILS Reaps Reward of Khrunichev Takeover|publisher=Satellite Finance|date=December 2009}}</ref> On 19 October 2011, [[ViaSat-1]] weighing 6740&nbsp;kg was lifted into GTO by the Proton-M/Briz-M Phase III.<ref>{{cite web|url=http://space.skyrocket.de/doc_sdat/viasat-1.htm|title=ViaSat 1|first=Gunter|last=Krebs |publisher=Gunter's Space Page}}</ref> === Light and Medium variants === Proton Light and Proton Medium were two proposed variants with a lower payload capacity at a reduced price. Originally proposed end of 2016, Proton Light was cancelled in 2017 {{Citation needed|date=May 2021}} and Proton Medium was put on "indefinite hold" in 2018.<ref>{{cite news|url=https://spacenews.com/proton-medium-international-launch-services-answer-to-falcon-9-put-on-indefinite-hold/|title=Proton Medium, International Launch Services' answer to Falcon 9, put on "indefinite hold"|work=[[SpaceNews]]|first=Caleb|last=Henry|date=August 30, 2018|access-date=August 31, 2018}}</ref> The variants were designed to reduce the cost for launching medium and small commercial communications satellites into Geostationary Transfer Orbit (GTO).<ref name=sn-20160913>{{cite web|url=http://spacenews.com/ils-unveils-two-proton-variants-sized-for-smaller-satellite |title=ILS unveils two Proton variants sized for smaller satellites|publisher=Space News|date=13 September 2016}}</ref> The variants were planned with a 2 + 1 stage architecture based on 3 stage Proton/Briz M, but dispensing with the 2nd stage and featuring minor lengthening of the other two stages. The Proton Light 1st stage was planned with 4 main engines and external tanks to the 6 used by Proton Medium and Proton-M. The cost was expected to be competitive with Ariane and SpaceX. The planned maiden flights were 2018 for Proton Medium and 2019 for Proton Light. They were expected to use [[Baikonur Cosmodrome]] Site 81/24 and would have required a new transporter-erector system and other ground infrastructure changes. The full-sized Proton-M can currently lift 6300&nbsp;kg into a standard Geostationary Transfer Orbit (GTO); Proton Medium was planned to lift 5000&nbsp;kg into a similar GTO while Proton Light was rated for 3600&nbsp;kg. The 3000–5000&nbsp;kg payload range includes all-electric and hybrid satellites that use ion thrusters to slowly make their way into geostationary orbit (GEO).<ref name="SpaceFlight101.com">{{cite web |url=http://spaceflight101.com/ils-introduces-proton-variants|title=ILS to expand Proton Rocket Family in Response to Changing Launch Market|publisher=SpaceFlight101.com|date=13 September 2016}}</ref> === Launch profile === In a typical mission, a Proton-M is accompanied by a [[Briz (rocket stage)|Briz-M]] upper stage. The Proton-M launches the orbital unit (that is: the payload, the payload adapter and the Briz-M) into a slightly suborbital trajectory. The first and second stages and the [[payload fairing]] crash into designated crash sites; the third stage crashes into the ocean. After the third stage separates, the orbital unit coasts for a brief period, then Briz-M performs its first firing to achieve [[Orbit insertion|orbital injection]] into a parking orbit with 51.5° [[Orbital inclination|inclination]], at 170&nbsp;km to 230&nbsp;km altitude (the Mission Planner's Guide also mentions 64.8° and 72.6° as standard inclinations for the parking orbit). Subsequently, the Briz-M performs [[orbital maneuver]]s to place the payload into either its final orbit or a transfer orbit. If a transfer orbit is used the final maneuver(s) are performed by the payload on its own propulsion system. == Reliability == {{stack|float=left|cellspacing=0|[[File:Proton-M Being Readied for Rollout, January 2005.jpg|left|thumb|Proton-M in assembly building awaiting rollout]]}} {{As of|2020|07|30}}, 111 Proton-M launches had occurred, of which 11 failed or partially failed, yielding a success rate of {{percent|100|111}}. Four of these failures were the results of problems with the Proton-M itself, six were caused by the [[Briz (rocket stage)|Briz-M]] upper stage malfunctioning and leaving cargo in a useless orbit (albeit on two instances the satellites were able to maneuver to correct orbit under their own propulsion), and one was the result of a [[Blok DM-03]] upper stage being incorrectly fueled, leaving the Proton too heavy to achieve orbit. === Notable launch failures === In September 2007, a Proton-M/Briz-M rocket carrying Japan's [[JCSAT-11]] communications satellite failed to achieve orbit, and fell in the [[Ulytau District]] of [[Kazakhstan]]. An investigation determined that first and second stages of the rocket had failed to separate, due to a damaged pyrotechnic cable.<ref>{{cite web|url=http://www.russianspaceweb.com/proton_jcsat11.html|title=Proton/JCSAT-11 launch failure |first=Anatoly|last=Zak|date=6 September 2007|access-date=29 July 2013|work=RussianSpaceWeb}}</ref> On 5 December 2010, the upper stage and payloads failed to reach orbital velocity due to overloading of the upper stage with 1500&nbsp;kg of liquid oxygen, resulting in the loss of three [[GLONASS]] satellites it was carrying.<ref>{{cite web|title=Russia clears Proton to resume flying in December|date=10 December 2010|publisher=Spaceflight Now|url=http://www.spaceflightnow.com/news/n1012/10protonrtf/}}</ref> In July 2013, a Proton-M/DM-03 carrying three [[GLONASS]] satellites failed shortly after liftoff.{{citation needed|date=December 2020}} The booster began pitching left and right along the vertical axis within a few seconds of launch. Attempts by the onboard guidance computer to correct the flight trajectory failed and ended up putting it into an unrecoverable pitchover. The upper stages and payload were stripped off 24 seconds after launch due to the forces experienced followed by the first stage breaking apart and erupting in flames. Impact with the ground occurred 30 seconds after liftoff. The preliminary report of the investigation into the July 2013 failure indicated that three of the first stage angular velocity sensors, responsible for [[Yaw (rotation)|yaw]] control, were installed in an incorrect orientation. As the error affected the redundant sensors as well as the primary ones, the rocket was left with no yaw control, which resulted in the failure.<ref>{{cite web|url=http://www.russianspaceweb.com/proton_glonass49.html|title=Russia's Proton crashes with a trio of navigation satellites|date=9 July 2013 |publisher=RussianSpaceWeb|access-date=10 July 2013}}</ref> Telemetry data also indicated that a pad umbilical had detached prematurely, suggesting that the Proton may have launched several tenths of a second early, before the engines reached full thrust. In May 2014, another Proton-M launch ended in failure, resulting in the loss of an [[Ekspress]] telecommunications satellite. Unlike the 2013 crash, this occurred more than nine minutes into the flight when one of the third stage verniers shut off, causing loss of attitude control. An automatic shutdown and destruct command was issued and the remains of the upper stages and payload impacted in northern China. An investigation committee concluded that the failure was most likely due to one of the turbopumps breaking off its mount, rupturing a propellant line and causing the vernier to lose thrust. In May 2015, a Proton-M with a Mexican telecommunications satellite, [[Mexican Satellite System|MexSat-1]], was lost due to problems with the third stage. Russian sources indicated that the problems had been the same as with the 2014 failure.<ref>{{cite web|url=https://slon.ru/posts/51567|title=Названа предварительная причина аварии "Протона" с мексиканским спутником|date=16 May 2015|publisher=slon.ru|access-date=16 May 2015}}</ref> An investigation determined that the third stage vernier engine [[RD-0214]] failed due to excessive vibration loads, which had been caused by an increasing imbalance of the rotor in the turbopump and concluded it was the same cause of a prior accident in 1988.<ref>{{cite web|url=http://www.spaceflightinsider.com/organizations/roscosmos/third-stage-engine-blamed-for-russian-proton-m-rocket-crash/|title=Third stage engine blamed for Russian Proton-M rocket crash - SpaceFlight Insider|website=www.spaceflightinsider.com|access-date=2017-06-01|date=June 2015}}</ref><ref>{{cite web |url=http://www.russianspaceweb.com/mexsat1.html|title=Proton mission with MexSat-1 satellite|website=www.russianspaceweb.com|access-date=2017-06-01}}</ref> In a June 2016 launch, one of the four second stage engines shut down prematurely. The Briz-M was able to make up for the resulting stage under-performance and deliver the [[List of Intelsat satellites|Intelsat 31]] satellite to the intended orbit. Pending an investigation, the rocket was grounded for the rest of 2016 and first half of 2017: Proton-M at that time planned to return to the launch pad around June 2017 to deliver the [[EchoStar|EchoStar-21]] satellite to orbit. On 28 January 2017, the Russian government announced, as a result of the investigation into the failure of [[Progress MS-04]], the recall of all Proton-M 2nd and 3rd stage engines produced by the [[Voronezh Mechanical Plant]], including the disassembly of three completed Proton rockets and a three and a half month suspension of flights.<ref>{{cite web |url=http://www.spacedaily.com/reports/Russia_to_check_space_flight_engines_over_faulty_parts_999.html|title=Russia to check space flight engines over faulty parts}}</ref> The investigation found that cheaper alternatives, unable to resist high temperatures, had been used in place of engine parts containing valuable minerals, and that production and certification documentation had been falsified.{{citation needed|date=December 2020}} Proton returned to flight 8 June 2017, a full year after the previous flight on 6 June 2016. === Upper stage malfunctions === Among the various Proton-M failures, some have been caused by the upper stages used to allow the rocket to deliver payloads to higher orbit, notably the failures in May 2014 and May 2015. At least five earlier launches also succumbed to problems with the Briz-M upper stage; [[Arab Satellite Communications Organization|Arabsat-4A]] in February 2006, [[AMC-14]] in March 2008, [[Ekspress AM4]] in August 2011, [[Telkom-3]] and [[Ekspress MD2]] in August 2012<ref>{{cite news|url=http://www.thehindu.com/news/international/article3737512.ece|title=Russian rocket fails to reach target orbit|date=7 August 2012|newspaper=The Hindu}}</ref> and [[Yamal-402]] in December 2012. All of the payloads were unusable except for Yamal-402, which was able to correct its orbit at the expense of several years' operational life, and [[AMC-14]] which was sold to the [[Federal government of the United States|US Government]] after SES determined that it couldn't complete its original mission. === Effect on government and industry === As a result of the July 2013, Proton-M launch failure, a major reorganization of the Russian space industry was undertaken. The [[United Rocket and Space Corporation]] was formed as a [[Joint-stock company|joint-stock]] corporation by the [[Government of Russia|government]] in August 2013 to consolidate the Russian [[spaceflight|space]] sector. Deputy Prime Minister [[Dmitry Rogozin]] said "the failure-prone space sector is so troubled that it needs state supervision to overcome its problems".<ref name=pa20130830>{{cite news|last=Messier|first=Doug|title=Rogozin: Russia to Consolidate Space Sector into Open Joint Stock Company|url=http://www.parabolicarc.com/2013/08/30/rogozin-interview-kommersant/|access-date=31 August 2013|newspaper=Parabolic Arc|date=30 August 2013}}</ref> Three days following the failure, the Russian government had announced that "extremely harsh measures" would be taken "and spell the end of the [Russian] space industry as we know it".<ref name=rbth20130703>{{cite news|last=Nilolaev|first=Ivan |title=Rocket failure to lead to space industry reform|url=http://rbth.ru/science_and_tech/2013/07/03/rocket_failure_to_lead_to_space_industry_reform_27729.html|access-date=1 September 2013|newspaper=Russia Behind The Headlines|date=3 July 2013}}</ref> == Environmental impact == Critics claim that Proton rocket fuel ([[unsymmetrical dimethylhydrazine]] (UDMH)) and debris created by Russia's space programme is poisoning areas of [[Russia]] and [[Kazakhstan]]. Residents claim that [[acid rain]] falls after some launches. Anatoly Kuzin, deputy director of the [[Khrunichev State Research and Production Space Center]], has however denied these claims, saying: "We did special research into the issue. The level of acidity in the atmosphere is not affected by the rocket launches [and] there is no data to prove any link between the illnesses, in [[Altai Town|Altai town]] and the influence of rocket fuel components or space activity of any kind".<ref name="BBC">{{cite news|url=https://www.bbc.co.uk/news/world-europe-19127713|title=Russians say space rocket debris is health hazard|publisher=BBC|access-date=7 August 2012|work=BBC News|date=7 August 2012|last1=Vassilieva|first1=Maria}}</ref> == See also == {{Portal|Spaceflight}} * [[Comparison of heavy lift launch systems]] * [[List of Proton launches]] == Notes == {{notelist}} == References == {{reflist}} {{Universal Rocket}} {{Expendable launch systems}} {{Russian launch vehicles}} [[Category:Universal Rocket (rocket family)]] [[Category:Space launch vehicles of Russia]] [[Category:Vehicles introduced in 2001]]'