View source for Engineering:Soyuz-7 (rocket)

{{short description|LOX and methane fueled}}
{{Infobox rocket
<!----Image (optional)---->
|image   =  <!--image filename (omit "Image:" prefix), required-->
|image_size  =  <!--Size of image (omit "px" suffix), optional, defaults to 270px-->
|caption =  <!--caption, optional-->
<!----Core parameters (required)---->
|name           = Soyuz-7<ref name=soyuz7-0717 /><!--Name(s) of the rocket, optional, defaults to page title-->
|function       =  <!--Purpose of the rocket, required-->
|manufacturer   = JSC SRC Progress<!--Manufacturer, required-->
|country-origin = Russia<!--country of origin, optional-->
<!----Costs (optional)---->
|pcost    =  <!--project cost, optional-->
|cpl      =  <!--cost per launch, optional-->
|alt-cpl  =  <!--cost in alternative currency, optional-->
<!----Dimensions (required)---->
|height       =  {{convert|46.5|m|abbr=on}}<ref name=rsw-soyuz5 /><!--height of the rocket in metres, use {{convert|HEIGHT|m|abbr=on}}, required-->
|diameter     =  {{convert|3.6|m|abbr=on}}<ref name=spaceresearchandtech-2013n3p47 /><!--core diameter in metres, use {{convert|DIAMETER|m|abbr=on}}, required-->
|width        =  <!--width if not axisymmetric, use {{convert|WIDTH|m|abbr=on}}, optional-->
|mass         =  {{convert|270000|kg|abbr=on}}<ref name=ria-1190701345 /><!--mass of rocket in kilograms, use {{convert|MASS|m|abbr=on}}, required-->
|stages       =  2<!--number of stages, not including boosters-->
<!----Payloads (optional)---->
|capacities =  <!--insert one of the following templates for each payload:-->
  {{Infobox rocket/payload
  |location =  [[Astronomy:Low Earth orbit|LEO]]<!--Target orbit/trajectory, required. Please use [[Astronomy:Geostationary transfer orbit|GTO]] or [[Astronomy:Low Earth orbit|LEO]] instead of just GTO or [[Astronomy:Low Earth orbit|LEO]].-->
  |kilos    =  {{convert|9|MT|abbr=on}}<ref name=ria-1190701345 /><!--Payload mass in kilograms, use {{convert|PAYLOAD|kg|abbr=on}}, required-->
  }}
<!----Associated rockets (optional)---->
|family      =  <!--rocket family, optional-->
|derivatives =  <!--derived rockets, optional-->
|comparable  =  Soyuz-2 (rocket)<!--similar, unrelated rockets, optional-->
<!----Launch history (required)---->
|status   =  <!--current status (eg. Active, Retired, etc), required-->
|sites    =  <!--launch centres and pads, required-->
|launches =  <!--total launches to date, optional-->
|success  =  <!--total successful launches, optional-->
|fail     =  <!--total failed launches, optional-->
|partial  =  <!--total number of launches resulting in partial failure (e.g. incorrect orbit but still usable), optional-->
|other_outcome =  <!--number of launches with unknown outcomes (or in progress), optional-->
|first    =  <!--date of first flight, optional-->
|last     =  <!--date of final flight, optional-->
|only     =  <!--launch date if only one was launched, optional-->
|payloads =  <!--associated payloads, optional-->
<!--Stages/boosters (optional)-->
|stagedata    =  <!--insert one of the following templates for each stage:-->
  {{Infobox rocket/stage
  |type       =  stage<!--booster or stage (must be in lower case)-->
  |diff       =  <!--variant of rocket this is used on, optional-->
  |stageno    =  First<!--position of stage in rocket, spelled out (eg. First, Second, etc), required-->
  |name       =  <!--name of the stage/booster, optional-->
  |number     =  <!--number of boosters, required if type = booster-->
  |length     =  <!--length of a single booster/stage in metres, use {{convert|LENGTH|m|abbr=on}}, optional-->
  |diameter   =  {{convert|3.6|m|abbr=on}}<ref name=spaceresearchandtech-2013n3p47 /><!--diameter of a single booster/stage in metres, use {{convert|DIAMETER|m|abbr=on}}, optional-->
  |width      =  <!--width of a single booster/stage if not axisymmetric, use {{convert|WIDTH|m|abbr=on}}, optional-->
  |empty      =  <!--empty mass of a single booster/stage in kilograms, use {{convert|EMPTYMASS|kg|abbr=on}}, optional-->
  |gross      =  <!--gross (fuelled) mass of a single booster/stage, use {{convert|GROSSMASS|kg|abbr=on}}, optional--> 
  |propmass   =  <!--propellant mass carried by a single booster/stage in kilograms, use {{convert|PROPMASS|kg|abbr=on}}, optional--> 
  |engines    =  RD-0164<ref name=spaceresearchandtech-2013n3p47 /><ref name=kbkha-annualreport2013 /><!--number and type of engines used on each individual booster/stage, required-->
  |solid      =  <!--set to "yes" (lowercase) to change Engines to Motor for solid motors-->
  |thrust     =  {{convert|3330|kN|abbr=on}}<ref name=kbkha-annualreport2014 /><!--thrust provided by a single booster/stage in kN, use {{convert|THRUST|kN|abbr=on}}, required-->
  |total      =  <!--total thrust for all boosters in kN, use {{convert|THRUST|kN|abbr=on}}, optional-->
  |SI         =  '''Sea Level''':321 seconds<br/>'''Vacuum''': 356 seconds<!--specific impulse of an individual booster/stage, in secs, optional-->
  |burntime   =  <!--burn time, required-->
  |fuel       =  CH<sub>4</sub> / [[Astronomy:LOX|LOX]]<ref name=ria-1190701345 /><!--fuel used in stage/boosters, required-->
  }}
  {{Infobox rocket/stage
  |type       =  stage<!--booster or stage (must be in lower case)-->
  |diff       =  <!--variant of rocket this is used on, optional-->
  |stageno    =  Second<!--position of stage in rocket, spelled out (eg. First, Second, etc), required-->
  |name       =  <!--name of the stage/booster, optional-->
  |number     =  <!--number of boosters, required if type = booster-->
  |length     =  <!--length of a single booster/stage in metres, use {{convert|LENGTH|m|abbr=on}}, optional-->
  |diameter   =  {{convert|3.6|m|abbr=on}}<ref name=spaceresearchandtech-2013n3p47 /><!--diameter of a single booster/stage in metres, use {{convert|DIAMETER|m|abbr=on}}, optional-->
  |width      =  <!--width of a single booster/stage if not axisymmetric, use {{convert|WIDTH|m|abbr=on}}, optional-->
  |empty      =  <!--empty mass of a single booster/stage in kilograms, use {{convert|EMPTYMASS|kg|abbr=on}}, optional-->
  |gross      =  <!--gross (fuelled) mass of a single booster/stage, use {{convert|GROSSMASS|kg|abbr=on}}, optional--> 
  |propmass   =  <!--propellant mass carried by a single booster/stage in kilograms, use {{convert|PROPMASS|kg|abbr=on}}, optional--> 
  |engines    =  RD-0169<ref name=ria-1190701345 /><!--number and type of engines used on each individual booster/stage, required-->
  |solid      =  <!--set to "yes" (lowercase) to change Engines to Motor for solid motors-->
  |thrust     =  {{convert|737|kN|abbr=on}}<ref name=kbkha-annualreport2014 /><!--thrust provided by a single booster/stage in kN, use {{convert|THRUST|kN|abbr=on}}, required-->
  |total      =  <!--total thrust for all boosters in kN, use {{convert|THRUST|kN|abbr=on}}, optional-->
  |SI         =  <!--specific impulse of an individual booster/stage, in secs, optional-->
  |burntime   =  <!--burn time, required-->
  |fuel       =  CH<sub>4</sub> / [[Astronomy:LOX|LOX]]<ref name=ria-1190701345 /><!--fuel used in stage/boosters, required-->
  }}
}}

The '''Soyuz-7''' ({{Lang-rus|'''Союз-7'''}}) is a launch family Russian [[Engineering:Rocket|rocket]]  proposed by JSC SRC Progress, the manufacturer and custodian of the [[Engineering:Soyuz (rocket family)|Soyuz]] family design,<ref name=rsw-soyuz5 /> within the Project '''Feniks''' ({{Lang-ru|'''Феникс'''|lit=Fenix}}). While all previous iterations of the Soyuz family had its roots firmly set on the [[Engineering:R-7 (rocket family)|R-7]] ICBM legacy, the Soyuz-7 is a complete new design from the ground up. It is based on a new propellant: [[Astronomy:LOX|LOX]] and liquid methane, uses a new tank structure, new propulsion, does away with the famous R-7 tulip and has [[Engineering:Thrust vectoring|thrust vector control]] in the main engine rather than using vernier engines.<ref name=rsw-soyuz5 /> It is also a scalable family with three versions covering the [[Engineering:Medium-lift launch vehicle|medium]] to [[Engineering:Heavy-lift launch vehicle|heavy]] payload ranges.<ref name=rsw-soyuz5 />

The project is considered as fundamental to assure access to space to Russia, since it is transitioning exclusively to the Angara family, and the Soyuz-7 would add redundancy in case of an Angara stand down.<ref name=ria-1190701345 /> The smallest version is a 270 tonnes rocket and is proposed as a replacement of the Soyuz-2 rocket, and has an expected payload to [[Astronomy:Low Earth orbit|LEO]] of 9 tonnes. It will use a single RD-0164 on the first stage, and a RD-0169 on the second.<ref name=sn-1025862519 /><ref name=tass-791963 /> The first engineering design is expected to be finalized by 2016,{{update after|2017}} and the first flight expected for 2022.<ref name=rt-312757 /> The use of just two stages for the base version, and the simplification of subsystems means a more reliable and cheaper launcher. In fact, the lightest version is expected to be cheaper than the Soyuz-2.<ref name=spaceflightinsider-20150820 />

==History==
During an interview with the kazakhstani magazine ''Space Research and Technologies'' during 2013, Mr. Kirilin, CEO of TSKB Progress, explained the conception of the project.<ref name=spaceflightinsider-20150820 /> When the [[Engineering:Rus-M|Rus-M]] project was cancelled, TSKB Progress started work on a methane fueled launch vehicle under the Roscosmos '''Magistral''' research program.<ref name=spaceflightinsider-20150820 /> This work was self funded by the company, and looked to replace the [[Engineering:Soyuz (rocket family)|Soyuz]] vehicle and keep the vehicle design capabilities within the company.

The venerable vehicle would be some 60 years old design by 2020 and it could not remain competitive with the new vehicles, like the [[Engineering:Falcon 9|Falcon 9]]. It was described by Progress CEO, Mr. Kirilin, as ''technologically and operationally hopelessly outdated''.<ref name=spaceflightinsider-20150820 /> It has conical sections, where each panel is unique, it uses six engines with 24 nozzles, most task include a lot of manual operations, it even requires five different fluids, [[Chemistry:Kerosene|kerosene]], [[Physics:Liquid oxygen|liquid oxygen]], [[Chemistry:Hydrogen peroxide|hydrogen peroxide]], gaseous [[Chemistry:Nitrogen|nitrogen]] and gaseous [[Chemistry:Helium|helium]]. Looking forward, the price of RG-1 fuel was going up, since it could only be distilled from a single oil field, that is expected to be depleted soon.<ref name=spaceflightinsider-20150820 />

The Soyuz-7 would use the same diameter for all sections of the rocket, {{convert|3.6|m|ft|abbr=on}}, use just liquid methane and [[Physics:Liquid oxygen|liquid oxygen]], have a single engine with a single nozzle per stage, and automate most tasks.<ref name=spaceflightinsider-20150820 /> But it could use the basic Soyuz pads and installations after some modifications. Liquid methane is cheap, Russia has ample reserves and it has a huge installed base. It also has some important thermal and polymerizing properties that paves the way for reusable rockets. The rocket was expected to use the KBKhA RD-0164 engine in the core stages, and a methane version of the also KBKhA's RD-0124 in the upper stage.<ref name=spaceflightinsider-20150820 />

During an August, 2015 interview with Ria Novosti, Mr. Kirilin stated that preliminary design was expected in 2015 or 2016,{{update after|2017}} that they will first develop the light version, that they expected to fly the first prototype in 2022 and that the propulsion would be the RD-0164 for the cores and the RD-0169 for the upper stage.<ref name=ria-1190701345 />

==Versions==
The Soyuz-7 would be designed to be a scalable family. As such it has three proposed versions:
* Basic version, designed to replace the Soyuz-2.1a/b rockets, uses a first and a second stage. It is expected to have a payload to a {{convert|200|km|nmi|abbr=on}} circular [[Astronomy:Low Earth orbit|LEO]] orbit of {{convert|9|MT|abbr=on}}.<ref name=progress-4608 /><ref name=rsw-soyuz5 />
* Design as a crew carrier vehicle that would use a central core and two equal cores on the side as boosters. It wouldn't have an air lighted seconds stage which eliminates air start risk. It is expected to have a payload to LEO of {{convert|16|MT|abbr=on}}.<ref name=progress-4608 /><ref name=rsw-soyuz5 />
* Heaviest version with maximum capability.<ref name=spacedigest-20150622 /> It is expected to have a payload to LEO of {{convert|25|MT|abbr=on}}.<ref name=progress-4608 /><ref name=rsw-soyuz5 />

==See also==
*[[Engineering:Soyuz programme|Soyuz programme]]
*[[Engineering:Soyuz (rocket family)|Soyuz rocket family]]
*{{annotated link|Engineering:Soyuz-5 (rocket)|Soyuz-5 rocket family}}
*{{annotated link|Engineering:Angara (rocket family)|Angara}}

==References==
{{Reflist|30em|refs=
<ref name=kbkha-annualreport2013>{{Cite report |date=2014-05-28 |title=ГОДОВОЙ ОТЧЕТ Акционерного общества «Конструкторское бюро химавтоматики» (АО КБХА) за 2013 год |trans-title="Chemical Automatics Design Bureau" (JSC KBKhA) Annual Report for 2013 |url=http://www.e-disclosure.ru/portal/FileLoad.ashx?Fileid=900387 |publisher=JSC KBKhA |page=37 |format=PDF |language=Russian |accessdate=2015-08-20}}</ref>
<ref name=kbkha-annualreport2014>{{Cite report |date=2015-05-22 |title=ГОДОВОЙ ОТЧЕТ Акционерного общества «Конструкторское бюро химавтоматики» (АО КБХА) за 2014 год |trans-title="Chemical Automatics Design Bureau" (JSC KBKhA) Annual Report for 2014 |url=http://www.e-disclosure.ru/portal/FileLoad.ashx?Fileid=1094198 |publisher=JSC KBKhA |page=43 |format=PDF |language=Russian |accessdate=2015-08-20}}</ref>
<ref name=progress-4608>{{cite web |url=http://www.samspace.ru/news/press_relizy/4638/ |title=Делегация «ЦСКБ-Прогресс» приняла участие в открытии международной выставки «ILA Berlin Airshow 2014» |trans-title= Samara Space Center participates in the International Exhibition «ILA Berlin Airshow 2014» |publisher=JSC SRC Progress |date=2014-05-06 |language=Russian |accessdate=2015-08-20}}</ref>
<ref name=ria-1190701345>{{cite web |url=http://ria.ru/interview/20150818/1190701345.html |title=РКЦ "Прогресс": летный образец ракеты "Союз-5" ожидаем к 2022 году |trans-title=RCC "Progress": expects to fly "Soyuz-5" prototype by 2022 |publisher=RIA Novosti |date=2015-08-18 |language=Russian |accessdate=2015-08-20}}</ref>
<ref name=rsw-soyuz5>{{cite web |url=http://www.russianspaceweb.com/soyuz5.html |title=Soyuz-5 rocket |last=Zak |first=Anatoly |publisher=RussianSpaceWeb |date=2014-07-31 |accessdate=2015-08-20}}</ref>
<ref name=rt-312757>{{cite web |url=https://www.rt.com/news/312757-progress-soyuz-5-rocket-kirilin/ |title=Brand-new Soyuz rocket powered by natural gas to be developed by 2022 |publisher=RT |date=2015-08-18 |accessdate=2015-08-20}}</ref>
<ref name=sn-1025862519>{{cite web |url=http://sputniknews.com/russia/20150818/1025862519.html |title=Russia to Build New Medium-Class Carrier Rocket by 2022 |publisher=Sputnik News |date=2015-08-18 |accessdate=2015-08-20}}</ref>
<ref name=spacedigest-20150622>{{cite web |url=http://spacedigest.net/en/articles/what-roscosmos-showed-and-said-during-the-paris-air-show |title=What Roscosmos showed, and said, during the Paris Air Show |date=2015-06-22 |publisher=Space Digest |accessdate=2015-08-20}}</ref>
<ref name=spaceflightinsider-20150820>{{cite web |url=http://www.spaceflightinsider.com/organizations/roscosmos/russia-build-new-eco-friendly-soyuz-5-rocket-2022/ |title=Russia to build new eco-friendly Soyuz-5 rocket by 2022 |last=Nowakowski  |first=Tomasz |date=2015-08-20 |accessdate=2015-08-20}}</ref>
<ref name=spaceresearchandtech-2013n3p47>{{cite journal |url=http://www.cosmos.kz/pdf/KIT_web%208.pdf |title="Союз" с метаном |trans-title=Soyuz on Methane |last=Voroncov |first=Dimitry |journal=Space Research and Technologies |year=2013 |number=3 (8) |pages=47–51 |format=PDF |language=Russian |accessdate=2015-08-20}}</ref>
<ref name=tass-791963>{{cite web |url=http://tass.ru/en/non-political/791963 |title=Russia's new rocket will be named Fenix — source |publisher=Russian News Agency TASS |date=2015-04-27 |accessdate=2015-08-20}}</ref>
<ref name=soyuz7-0717>{{cite web |url=https://ria.ru/science/20170718/1498685067.html |title=Российскую ракету с метановыми двигателями хотят назвать "Союз-7" |trans-title= Russian rocket with methane engine could be named Soyuz-7 |publisher=RIA |date=2017-07-18 |language=Russian |accessdate=2017-11-23}}</ref>
}}

==External links==
*[http://www.russianspaceweb.com/soyuz5.html Anatoly Zak's page on the Soyuz-7]

{{Russian launch vehicles}}
{{Expendable launch systems}}

{{DEFAULTSORT:Soyuz-7 (Rocket)}}
[[Category:Space launch vehicles of Russia]]

{{Sourceattribution|Soyuz-7 (rocket)|1}}