RD-253

{{Short description|Soviet engine design used on the first stage of Proton rockets}} {{Infobox rocket engine | name = RD-253 | image = Mockup rocket motor RD-275 Salon du Bourget 2013 DSC 0062.jpg | caption = Mock-up of a RD-275 rocket motor at the [[Paris Air Show]] in 2013 | country_of_origin = {{hlist|[[Soviet Union]]|[[Russia]]}} | date = | first_date = '''RD-253''': 1965 '''RD-275''': 1995 '''RD-275М''': 2007 | last_date = | designer = [[NPO Energomash]], [[Valentin Glushko]] | manufacturer = [[Proton-PM]] | purpose = First stage booster | associated = [[Proton (rocket)|Proton]] | predecessor = | successor = RD-254, RD-256, RD-275, RD-275М | status = Operational | type = liquid | oxidiser = {{chem2|N2O4|link=Dinitrogen tetroxide}} | fuel = [[Unsymmetrical dimethylhydrazine|UDMH]] | mixture_ratio = 2.67 | cycle = [[Staged combustion cycle (rocket)|Staged combustion]] | pumps = | description = | combustion_chamber = 1 | nozzle_ratio = 26.2 | thrust(Vac) = '''RD-253''': {{cvt|1630|kN}} '''RD-275''': {{cvt|1750|kN}} '''RD-275М''': {{cvt|1832|kN}} | thrust(SL) = '''RD-253''': {{cvt|1470|kN}} '''RD-275''': {{cvt|1590|kN}} '''RD-275М''': {{cvt|1671|kN}} | throttle_range =  | thrust_to_weight = 156.2 | chamber_pressure = '''RD-253''': {{cvt|14.7|MPa|psi bar}} '''RD-275''': {{cvt|15.7|MPa|psi bar}} '''RD-275M''': {{cvt|16.5|MPa|psi bar}} | specific_impulse = | specific_impulse_vacuum = '''RD-253''': 316s '''RD-275''': 316s '''RD-275M''': 315.8s | specific_impulse_sea_level = '''RD-253''': 285s '''RD-275''': 287s '''RD-275M''': 288s | total_impulse = | burn_time = | restarts =  | gimbal = 7.5°, single plane | length = {{cvt|3|m}} | diameter = {{cvt|1.5|m}} | dry_weight = '''RD-253''': {{cvt|1080|kg}} '''RD-275''': {{cvt|1070|kg}} '''RD-275M''': {{cvt|1070|kg}}

| references = <ref name=npoem-rd253 /><ref name=ea-rd211d48 /><ref name=ea-rd253 /><ref name=protonpm-rd276 /><ref name=ea-protonk /><ref name=rsw-protonhist /><ref name=rsw-rd353 /> | notes = }}

The '''RD-253''' ({{Langx|ru|Ракетный Двигатель-253|Raketnyy Dvigatel-253|Rocket Engine 253}}) and its later variants, the '''RD-275''' and '''RD-275M''', are [[liquid-propellant rocket]] [[rocket engine|engines]] developed in the [[Soviet Union]] by [[NPO Energomash|Energomash]]. The engines are used on the first stage of the [[Proton (rocket)|Proton]] launch vehicle and use an oxidizer-rich [[Staged combustion cycle (rocket)|staged combustion]] cycle to power the turbopumps. The engine burns a [[Hypergolic propellant|hypergolic]] mixture of [[unsymmetrical dimethylhydrazine]] (UDMH) fuel with [[dinitrogen tetroxide]] ({{N2O4}}) oxidizer, which are highly toxic, but storable at room temperature.

== History == Development of the RD-253 started in 1961. Preliminary investigations and development of the engine and its further production was performed under the guidance of [[Valentin Glushko]] and finished in 1963. The RD-253 uses an [[Staged combustion cycle (rocket)#Oxidizer-rich staged combustion|oxidiser-rich staged combustion]] cycle. It was used for the first time in July 1965, when six engines powered the first stage of the [[Proton (rocket family)|Proton]] rocket. Development and production of RD-253 was a qualitative leap forward for rocketry of that time by achieving high levels of [[thrust]], [[specific impulse]] and pressure in the [[combustion chamber]]. This engine is one of the most reliable engines in the [[USSR]] and modern [[Russia]].

As the first stage of the [[Proton-K]] rocket used six RD-253 engines, the system played a pivotal role in Russian [[space mission]]s when this rocket was chosen as a carrier, including the following programs: [[Luna programme|"Luna"]], "[[Venera]]", [[Mars probe program|"Mars probe"]], crewed [[orbital station]]s [[Salyut program|"Salyut"]], "[[Mir]]", and it launched several principal modules for [[ISS]]. It was widely used for the launches of heavy satellites.<ref name=npoem-rd253 /><ref name=ea-protonk /> The last RD-253 rocket engine was used on a Proton-K rocket and launched on March 30, 2012.<ref name=rsw-protonhist />

Since the original development of the engine, several modifications were designed that were not flown. One of them was the RD-256 engine, for which development stopped on experimental models. It was not used in flights and was designed for a cancelled vehicle.<ref name=lprd-rd253 /> The RD-254 variant was supplied with an extended nozzle for use in vacuum.

== Current state and development == All rights to sell and employ the RD-253 for [[Proton (rocket)|Proton]] rocket are held by [[NPO Energomash|Energomash]] which produces it in [[Perm, Russia|Perm]], [[Russia]].

The modification '''RD-275''' (14D14) appeared as the result of development in 1987–1993, with the purpose to achieve a more powerful version of the engine. Its 7.7% higher thrust was reached by raising pressure in the [[combustion chamber]] and enabled an increase of [[Payload (air and space craft)|payload]] mass to [[Geostationary orbit|geostationary orbit (GEO)]] up to more than {{convert|6000|kg|abbr=on}}. The successful maiden flight of a [[Proton (rocket)|Proton]] rocket with the new engine was completed in 1995.

[[NPO Energomash|Energomash]] started the development of next more powerful version of engine in 2001. It has 5.2% higher thrust and has the designation 14D14M ('''RD-275M'''). It was designed to allow the rocket to deliver {{convert|150|kg|abbr=on}} more payload to [[Geostationary orbit|GEO]].<ref name=npoem-rd253 />

In the period from 2002 to 2003 years some experimental work was completed with this version of the engine. It included four test firings of three experimental RD-275M with a total time of 735[[second|s]]. In the middle of 2005, this engine went into production by government commission. The first launch of a [[Proton-M]] with 14D14M engines was launched on July 7, 2007.<ref name=npoem-rd253 />

The final version RD-275M is sometimes designated as RD-276, but through 2009 the name RD-275M (14D14M) was more common.<ref name=npoem-rd253 /><ref name=protonpm-rd276 /> Some sources{{which|date=January 2015}} points out the cost of production per engine as much as 1.5 million [[USD]] and sometimes calls some lower figures around 1 million [[USD]] per unit.{{citation needed|date=January 2015}}

== Versions == During the years there have been many versions of this engine: * '''RD-220''': Initial proposal for the [[N1 (rocket)|N-1]] first stage.<ref name=npoem-el /> * '''RD-221''': Initial proposal for the [[N1 (rocket)|N-1]] second stage.<ref name=npoem-el /> * '''RD-222''' ([[GRAU]] Index '''11D41'''): Development program for the [[N1 (rocket)|N-1]] first stage.<ref name=npoem-el /> * '''RD-223''' ([[GRAU]] Index '''11D42'''): Development program for the [[N1 (rocket)|N-1]] second stage.<ref name=npoem-el /> * '''RD-253''' ([[GRAU]] Index '''11D43'''): Serial production version for the [[Proton-K|Proton]] (8K62) first stage. Was proposed for the [[N1 (rocket)|N-1]] first stage. * '''RD-253F''' ([[GRAU]] Index '''11D43F'''): Project for [[R-36 (missile)#R-36M (SS-18) variants|R-36M]] (15А14) first stage.<ref name=npoem-el /> * '''RD-254''' ([[GRAU]] Index '''11D44'''): Project for [[Universal Rocket#UR-700|UR-700]] third stage and for [[Proton-K|Proton]] and [[N1 (rocket)|N-1]] second stages, it was a RD-253 high-altitude version. * '''RD-275''' ([[GRAU]] Index '''14D14'''): Serial production for [[Proton-M]] first stage. RD-253 with increased thrust by 8%.<ref name=npoem-el /> * '''RD-276''' ([[GRAU]] Index '''14D14М'''): Serial production for [[Proton-M]] first stage. Sometimes previously called RD-275M. Improved RD-275.<ref name=npoem-el />

{| class="wikitable" |+ RD-253 Family of Engines<ref name="npoem-el" /> |- style="vertical-align:top;" ! Engine ! RD-220 ! RD-221 ! RD-222 {{Small|(11D41)}} ! RD-223 {{Small|(11D42)}} ! RD-253 {{Small|(11D413)}} ! RD-253F {{Small|(11D413F)}} ! RD-254 {{Small|(11D44)}} ! RD-275 {{Small|(14D14)}} ! RD-275M {{Small|(RD-276, 14D14M)}}<ref name=protonpm-rd276 /> |- !Development | colspan="2" | 1960 || colspan="2" | 1960-1961 || 1962-1966 || 1966-1967 || 1961-1963 || 1987-1993 || 2001-2005 |- ! Combustion Chamber Pressure | colspan="5" |{{convert|14.7|MPa|psi|abbr=on}}|| {{convert|16.9|MPa|psi|abbr=on}} || {{convert|14.7|MPa|psi|abbr=on}} || {{convert|15.7|MPa|psi|abbr=on}} || {{convert|16.5|MPa|psi|abbr=on}} |- ! Thrust (Vacuum) |{{convert|1074|kN|lbf|abbr=on}} || {{convert|1120|kN|lbf|abbr=on}} || {{convert|1634|kN|lbf|abbr=on}} || {{convert|1700|kN|lbf|abbr=on}} || {{convert|1635|kN|lbf|abbr=on}} || {{convert|1870|kN|lbf|abbr=on}} || {{convert|1720|kN|lbf|abbr=on}} || {{convert|1750|kN|lbf|abbr=on}} || {{convert|1832|kN|lbf|abbr=on}} |- ! Thrust (Sea Level) |{{convert|947|kN|lbf|abbr=on}} || N/A || {{convert|1471|kN|lbf|abbr=on}} || N/A || {{convert|1474|kN|lbf|abbr=on}} || {{convert|1720|kN|lbf|abbr=on}} || N/A || {{convert|1590|kN|lbf|abbr=on}} || {{convert|1671|kN|lbf|abbr=on}} |- ! Specific Impulse (Vacuum) |{{convert|306|isp|abbr=on}} || {{convert|318|isp|abbr=on}} || {{convert|302|isp|abbr=on}} || {{convert|314|isp|abbr=on}} || {{convert|316|isp|abbr=on}} || {{convert|317|isp|abbr=on}} || {{convert|328|isp|abbr=on}} || {{convert|316|isp|abbr=on}} || {{convert|315.8|isp|abbr=on}} |- ! Specific Impulse (Sea Level) |{{convert|270|isp|abbr=on}} || N/A || {{convert|272|isp|abbr=on}} || N/A || {{convert|285|isp|abbr=on}} || {{convert|290|isp|abbr=on}} || N/A || {{convert|287|isp|abbr=on}} || {{convert|288|isp|abbr=on}} |- ! Height |{{convert|2600|mm|in|abbr=on}} || {{convert|4200|mm|in|abbr=on}} || {{convert|3470|mm|in|abbr=on}} || {{convert|5050|mm|in|abbr=on}} || {{convert|3000|mm|in|abbr=on}} || {{convert|2700|mm|in|abbr=on}} || {{convert|4000|mm|in|abbr=on}} || {{convert|3050|mm|in|abbr=on}} || {{convert|3050|mm|in|abbr=on}} |- ! Diameter |{{convert|1300|mm|in|abbr=on}} || {{convert|2400|mm|in|abbr=on}} || {{convert|1460|mm|in|abbr=on}} || {{convert|2530|mm|in|abbr=on}} || {{convert|1500|mm|in|abbr=on}} || {{convert|1490|mm|in|abbr=on}} || {{convert|2600|mm|in|abbr=on}} || {{convert|1500|mm|in|abbr=on}} || {{convert|1500|mm|in|abbr=on}} |- !Intended Use | [[N1 (rocket)|N-1]] first stage || [[N1 (rocket)|N-1]] second stage || [[N1 (rocket)|N-1]] first stage || [[N1 (rocket)|N-1]] second stage || [[Proton-K|Proton]] (8K62) first stage || [[R-36 (missile)#R-36M (SS-18) variants|R-36M]] (15А14) first stage || [[Universal Rocket#UR-700|UR-700]] third stage, [[Proton-K|Proton]] and [[N1 (rocket)|N-1]] second stages || [[Proton-M]] first stage || [[Proton-M]] first stage |- !Status | colspan="4" | Project (Abandoned) || Retired || colspan="2" | Project (Abandoned) || Retired || In Production |}

== See also == * [[Proton (rocket)|Proton]] - uses RD-275 * [[Rocket engine]]

=== References === {{Reflist|refs= <ref name=ea-protonk>{{cite web |url=http://www.astronautix.com/lvs/protonk.htm |archive-url=https://web.archive.org/web/20100822083221/http://www.astronautix.com/lvs/protonk.htm |url-status=dead |archive-date=August 22, 2010 |title=Proton-K |website=Encyclopedia Astronautica |access-date=2015-07-07}}</ref> <ref name=ea-rd211d48>{{cite web |url=http://www.astronautix.com/engines/rd211d48.htm |title=RD-253-11D48 |website=Encyclopedia Astronautica |access-date=2015-07-07 |url-status=dead |archive-url=https://web.archive.org/web/20160304061218/http://www.astronautix.com/engines/rd211d48.htm |archive-date=2016-03-04 }}</ref> <ref name=ea-rd253>{{cite web |url=http://www.astronautix.com/engines/rd253.htm |title=RD-253 |website=Encyclopedia Astronautica |access-date=2015-07-07 |url-status=dead |archive-url=https://web.archive.org/web/20150824113758/http://www.astronautix.com/engines/rd253.htm |archive-date=2015-08-24 }}</ref> <ref name=lprd-rd253>{{cite web |url=http://www.lpre.de/energomash/RD-253/index.htm |title=RD-253 (11D43) and RD-275 (14D14) |language=ru |access-date=2015-07-07}}</ref> <ref name=npoem-el>{{cite web |url=http://www.npoenergomash.ru/netcat_files/File/Table_of_Engines.docx |title=NPO Energomash list of engines |publisher=[[NPO Energomash]] |url-status=dead |archive-url=https://web.archive.org/web/20141107202512/http://www.npoenergomash.ru/netcat_files/File/Table_of_Engines.docx |archive-date=7 November 2014}}</ref> <ref name=npoem-rd253>{{cite web |url=http://www.npoenergomash.ru/eng/dejatelnost/engines/rd253/ |title=RD-253 |publisher=[[NPO Energomash]] |url-status=dead |archive-url=https://web.archive.org/web/20150405185423/http://www.npoenergomash.ru/eng/dejatelnost/engines/rd253/ |archive-date=5 April 2015}}</ref> <ref name=protonpm-rd276>{{cite web |url=http://www.protonpm.ru/creator/production/produce_and_services/pg1/84/ |title=Liquid rocket engine RD-276 |publisher=Proton-PM |access-date=6 July 2015 |archive-date=15 January 2022 |archive-url=https://web.archive.org/web/20220115224122/https://protonpm.ru/creator/production/produce_and_services/pg1/84/ |url-status=dead }}</ref> <ref name=rsw-protonhist>{{cite web|url=http://www.russianspaceweb.com/proton_history.html |title=Proton History |website=RussianSpaceWeb |first=Anatoly |last=Zak |access-date=2015-07-07}}</ref> <ref name=rsw-rd353>{{cite web |url=http://www.russianspaceweb.com/rd253.html |title=2015-07-07 |website=RussianSpaceWeb |first=Anatoly |last=Zak |access-date=2015-07-07}}</ref> }}

[[Category:Rocket engines of Russia]] [[Category:Rocket engines of the Soviet Union]] [[Category:Rocket engines using hypergolic propellant]] [[Category:Rocket engines using the staged combustion cycle]] [[Category:Energomash rocket engines]]