View source for RD-120

{{Short description|Soviet (now Russian) liquid rocket engine}}
{{infobox rocket engine
  |name                      = RD-120 (РД-120)
  |image                     = 
  |image_size                    = 
  |caption                   = 
  |country_of_origin         = [[USSR]]/[[Russia]]
  |date                      = 
  |manufacturer              = [[Yuzhmash]]
  |designer                  = [[NPO Energomash]],  V.K.Chvanov, V.P. Radovsky
  |status                    = Operational
  |purpose                   = Upper stage
  |type                      = liquid
  |fuel                      = [[RG-1 (propellant)|RP-1]]
  |oxidiser                  = [[LOX]]
  |cycle                     = [[Staged combustion cycle]]
  |thrust(Vac)               = '''Standard:''' {{convert|834|kN|abbr=on}}<br />
'''Uprated:''' {{convert|912|kN|abbr=on}}
  |specific_impulse_vacuum   = {{convert|350|isp|abbr=on}}
  |burn_time                 = 315 seconds
  |chamber_pressure          = '''Standard:''' {{convert|162.8|bar|MPa|abbr=on}}<br />
'''Uprated:''' {{convert|178.1|bar|MPa|abbr=on}}
  |thrust_to_weight          = '''Standard:''' {{nts|75.55}}<ref group="note"><math>\frac{833,565\ \mathrm{N}}{(1,125\ \mathrm{kg})(9.807\ \mathrm{m/s^2})}=75.55</math></ref><br />
'''Uprated:''' {{nts|82.66}}<ref group="note"><math>\frac{912,018\ \mathrm{N}}{(1,125\ \mathrm{kg})(9.807\ \mathrm{m/s^2})}=82.66</math></ref>
  |length                    = {{convert|3.87|m|ft|abbr=on}}
  |diameter                  = {{convert|1.95|m|ft|abbr=on}}
  |dry_weight                = {{convert|1125|kg|lb|abbr=on}}
  |used_in                   = [[Zenit-2]], [[Zenit-3SL]]
  |references      =<ref name=npoem-rd120 /><ref name=npoem-el /><ref name=k204-wiki2emash />
  |notes           =
}}
The '''RD-120''' ({{Langx|ru|Ракетный Двигатель-120|Raketnyy Dvigatel-120|Rocket Engine 120}}, [[GRAU index]]: '''11D123''') is a [[Liquid-propellant rocket|liquid]] [[upper stage]] [[rocket engine]] burning [[RG-1 (propellant)|RG-1]] (refined [[kerosene]]) and [[LOX]] in an [[Staged combustion cycle (rocket)|oxidizer rich staged combustion]] cycle with an [[Rocket propellant#Mixture ratio|O/F ratio]] of 2.6.<ref name=npoem-el /><ref name=k204-wiki2emash /><ref name=aviadvigatel /> It is used in the second stage of the [[Zenit (rocket family)|Zenit]] family of launch vehicles.<ref name=npoem-rd120 /> It has a single, fixed combustion chamber and thus on the Zenit it is paired with the [[RD-8]] [[Vernier thruster|vernier engine]]. The engine was developed from 1976 to 1985 by [[NPO Energomash]] with V.P. Radovsky leading the development.<ref name=k204-wiki2emash /> It is manufactured by, among others, [[Yuzhmash]] in [[Ukraine]].<ref name=yuzhmash-rd120 />

It should not be confused with the [[RD-0120]], which is a discontinued LOX/hydrogen rocket engine that was used in the [[Soviet]] [[Energia (rocket)|Energia]] launch system.

==History==
During the [[Buran programme]] initial development of the 11D77 &mdash;the launch vehicle later known as [[Zenit (rocket family)|Zenit]]&mdash;, [[Chemical Automatics Design Bureau|KBKhA]] had been assigned the development of the second stage engine, as they had done for the [[Proton (rocket)|Proton]] and [[Soyuz (rocket)|Soyuz]] vehicles. But given the difficulties for NPO Energomash in developing the RD-123 (which would later be known as the [[RD-170]]), they ceded the hydrogen / oxygen sustainer engine development to KBKhA. This project, the analog of the [[SSME]], was project RD-130 within NPO Energomash. But when KBKhA tackled the development, named it '''[[RD-0120|RD-''0''120]]''', a name that is always a source of confusion with the engine of the current article. In exchange for them tackling the difficult development of the cryogenic propellant engine, Energomash assumed the responsibility of developing the second stage engine of the 11D77, which would eventually be known as the '''RD-120'''.<ref name=hendrickx2007p66 /> The fact that the RD-120 and the RD-0120 had this intertwined conception, within the same program, and with a swap of designer bureaus, does not help to avoid the confusion.

On March 16, 1976 the Government passed a resolution for the development of Zenit, the RD-171 and RD-120.<ref name=npoem-milestones /> By April 1976, [[Yuzhnoye Design Office|Yuzhnoye]] supplied NPO Energomash with the final requirements for the 11D77 first and second stage propulsion. One of the desirable effects of consolidating the first and second stage propulsion on the same designer, was that they could learn their lessons on staged combustion engines on the smaller and simpler upper stage engine, and then apply them to the bigger and more innovative first stage RD-170. NPO Energomash, had already worked on a prototype kerosene / oxygen staged combustion engine in that range, based on the [[RD-263|RD-268]] hypergolic engine, which was already under serial production with [[Yuzhmash]].<ref name=hendrickx2007p79 />
<ref name=npoem-history /> In February, 1977, the preliminary design of the RD-120 was finished.<ref name=npoem-milestones /> And on January 31, 1979 the first fire test of the RD-120 was performed.<ref name=npoem-milestones />

The RD-120 had a complicated debut, with the second stage failing on its first (April 13, 1985), second (June 21, 1985) and fourth (December 28, 1985) flights. While only the first failure could be attributed to the RD-120 &mdash;the propellant flow regulator had a leak and the stage ran out of propellant before being orbital&mdash;, the program initial performance was quite troubling. Eventually it proved its worth, and by December 1987 the RD-120 (and the Zenit) were considered commissioned.<ref name=npoem-milestones /> But in the years of the Soviet dissolution, the second stage failed twice in a row on August 30, 1991 and February 5, 1992. Zenit had other second stage failures, but only the first one has ever been attributed directly to the RD-120 itself.<ref name=slr-zenit />

During 1990, the NPO Energomash Head of the Propulsion Department, and leading designer, V.K.Chvanov, was awarded the State Prize for the creation of RD-120.<ref name=npoem-milestones />

In October 1992, [[Pratt & Whitney]] signed an agreement with NPO Energomash to sale and represent their line of engine in the United States.<ref name=nasa-x34/> During the initial version of the [[X-34]] program, the one trying to develop a reusable launch vehicle for small payloads through a public/private association, the RD-120 was seriously considered for the [[Boeing 747|747]] air-launched first stage. The RD-120 offered the best price and performance, and was the preferred choice of [[Orbital Sciences Corporation|Orbital Sciences]].<ref name=nasa-x34/> In fact, on October 11, 1995, the RD-120 was fired on the U.S. and thus became the first Russian rocket engine actively in production to be fired in American soil.<ref name=pw-a017591005/> This version of the engine, would mainly differ from the Zenit in the addition of a [[Gimbaled thrust|gimbal]] mount that would enable it to offer [[thrust vectoring|TVC]]. This version would be known as the '''RD-120M'''.<ref name=pw-a017591005/> The second private partner in the X-34 program, [[Rockwell International]], wanted to use their own engine, the [[RS-27]]. And given the constrained schedule and budget of the program, the engine selection was not able to be resolved and the program cancelled and reimplemented as the pure NASA research program that the X-34 was later known for.<ref name=nasa-x34/>

Also during the 1990s, the Chinese acquired two or three models of the RD-120, and possibly some documentation.<ref name=wl-07kyiv2491 /><ref name=sd-lm5 /> This enabled them to bootstrap their indigenous kerosene staged combustion engine program, the [[YF-100]] and [[YF-115]].<ref name=sd-lm5 />

The RD-120 had significant margins built in, which allowed between 2001 and 2003 to develop a modernized 'Uprated' or 'Forced' version of the engine for [[Sea Launch]] which increased thrust 10% to {{convert|912|kN|lbf|abbr=on}}.<ref name=npoem-history /> It also incorporated many improvements, which allowed it to increase chamber pressure and thrust without additional weight gain.<ref name=npoem-rd120 /> It still has a 5% extra margin, extended the design life to 4260 seconds, the number of ignitions to 19 and allows to consider it as a base for a reusable rocket, the engine is still not capable of restarting inflight. After a program that used 4 test engines and performed 28 hot fire tests with an accumulated running time of 8,135 seconds, the engine was qualified for flight.<ref name=npoem-history/> Testing started in March 2004 and it had its debut flight on February 15, 2006 where it successfully orbited [[EchoStar X]].<ref name=hendrickx2007p410 /><ref name=gunter-zenit3 />

==Versions==
This engine has had two operative versions and some proposed variations:
* '''RD-120''' ([[GRAU]] Index '''11D123'''): Original version developed for the [[Zenit-2]] second stage.<ref name=npoem-rd120 /> The main characteristics is that it uses a vertical turbopump, since the fuel tank is a torus and the engine has to fit in the center hole.<ref name=k204-wiki2emash /><ref name=rsw-zenits2 />
* '''RD-120 (augmented thrust)''' ([[GRAU]] Index '''11D123'''): Thrust augmented version developed for the [[Zenit-3SL]] second stage.<ref name=npoem-rd120 /><ref name=npoem-el /> Some authors identified it as the RD-120M ([[GRAU]] Index 11D123M).
* '''RD-120K''': Project of unknown first stage project. Had reduced expansion area and the subsystem arrangements was done to reduce total length.<ref name=k204-wiki2emash /> It had enough development done that it actually performed some fire tests.<ref name=npoem-rd120 /><ref name=npoem-el /><ref name=ea-rd120k />
* '''RD-120M''': Version proposed for the [[X-34]] program. It added a gimbaled mount, and was test fired in the USA.<ref name=nasa-x34 /><ref name=pw-a017591005 />
* '''RD-120U''': Version proposed for the ULV-22.<ref name=b14643-ulv22 />
* '''RD-146''' <ref>{{Cite web|url=http://www.astronautix.com/r/rd-146.html|archive-url=https://web.archive.org/web/20161228032615/http://astronautix.com/r/rd-146.html|url-status=dead|archive-date=December 28, 2016|title = RD-146}}</ref>
* '''RD-182''': [[Methane]] / [[LOX]] version of the RD-120K. Proposed for the Riksha launch vehicle project for the [[Makeyev Rocket Design Bureau]].<ref name=ea-rd182 /><ref name=b14643-rikshadesc /><ref name=b14643-rikshaprop />
* '''RD-182M''': [[LNG]] / [[LOX]] version of the RD-182. Proposed for the Vozdushnyy Start launch vehicle project.<ref name=ea-rd182m />
* '''RD-870''': Ukrainian version of RD-120K with Russian-produced combustion chamber replaced with modified [[RD-263]] engines from stocks, being developed by [[Yuzhnoye Design Bureau]] for use in the first stage of [[Cyclone-4M]] SLV.<ref name="ZakRD870">{{Cite web|url=http://www.russianspaceweb.com/rd870.html|title = RD-870 could become Ukraine's first booster engine}}</ref>
{| class="wikitable"
|+ RD-120 Family of Engines
|-
!Name
!RD-120
!RD-120<br />(augmented thrust)
!RD-120K
!RD-870
|-
!AKA
|11D123 || 11D123<br />11D123M? ||
|-
!Development years
|1976–1985 || 2001–2003 || 1986– || 2016–
|-
!Engine Type
|colspan="4" style="text-align: center;"| [[Staged combustion cycle|Oxidizer Rich Stage Combustion]] [[upper stage]] [[Liquid-propellant rocket|liquid]] [[rocket engine]]
|-
!Propellant
|colspan="4" style="text-align: center;"| [[RP-1|RG-1]]/[[LOX]] (O/F 2.6)
|-
!Chamber Pressure
|{{convert|16.28|MPa|psi|abbr=on}} || {{convert|17.81|MPa|psi|abbr=on}} || {{convert|17.63|MPa|psi|abbr=on}} ||  {{convert|160|kgf/cm2|MPa|order=flip|abbr=on}}
|-
!Thrust (Vac)
|{{convert|833.6|kN|lbf|abbr=on}} || {{convert|912|kN|lbf|abbr=on}} || {{convert|853.2|kN|lbf|abbr=on}} ||  {{convert|88.46|tf|kN|order=flip|abbr=on}}
|-
!Thrust (SL)
| N/A || N/A || {{convert|784.5|kN|lbf|abbr=on}} ||  {{convert|79.6|tf|kN|order=flip|abbr=on}}
|-
!Isp (Vac)
|{{convert|350|isp|abbr=on}} || {{convert|350|isp|abbr=on}} || {{convert|330|isp|abbr=on}} || {{convert|332|isp|abbr=on}}
|-
!Isp (SL)
| N/A || N/A || {{convert|304.4|isp|abbr=on}} || {{convert|298|isp|abbr=on}}
|-
!Throttle
| 70–110% || 70–110% || 50–105% || 98.5–101.5%
|-
!Nozzle Expansion
| 114.5 || 114.5 || 49.6 || N/A
|-
!Burn time
|290 seconds || 290 seconds || 305 seconds || 200 seconds
|-
!Engine life
|2,200 seconds || 2,200 seconds || 2,200 seconds || N/A
|-
!Length
|{{convert|3872|mm|in|abbr=on}} || {{convert|3872|mm|in|abbr=on}} || {{convert|2435|mm|in|abbr=on}} ||  {{convert|2746|mm|in|abbr=on}}
|-
!Diameter
|{{convert|1954|mm|in|abbr=on}} || {{convert|1954|mm|in|abbr=on}} || {{convert|1400|mm|in|abbr=on}} ||  {{convert|1436|mm|in|abbr=on}}
|-
!Weight
|{{convert|1125|kg|lb|abbr=on}} || {{convert|1125|kg|lb|abbr=on}} || {{convert|1080|kg|lb|abbr=on}} || {{convert|1280|kg|lb|abbr=on}}
|-
!Used on
|[[Zenit-2]] Second Stage || [[Zenit-3SL]] Second Stage || Project || [[Cyclone-4M]] First Stage
|-
!First Launch
|1985-04-13 || 1999-03-28 || N/A || N/A
|-
!Status
|In Production|| In Production || Project || Project
|-
!References
|colspan="4" style="text-align: left;"|<ref name=npoem-rd120 /><ref name=npoem-el /><ref name=k204-wiki2emash /><ref name=aviadvigatel /><ref name=yuzhmash-rd120 /><ref name="ZakRD870" />
|-
|}

==Technological derivatives==

[[File:RD-120 Family.svg|thumb|right|upright=2|The family tree of the RD-120]]

Not considering straight variations of the RD-120, this very influential engine has been the foundations of many engines spanning derivatives in four countries. The [[Ukraine|Ukrainian]] [[RD-801]] and [[RD-810]], the [[China|Chinese]] [[YF-100]] and [[YF-115]], as well as the Indian [[SCE-200]] can be traced directly back to the RD-120. The Soviet/Russian [[RD-170]] family of engines base developed on the lessons learned from the RD-120 project.

===RD-170 family===
As stated in the History section, the RD-120 was used as the first practical application of the [[Staged combustion cycle (rocket)|oxidizer rich staged combustion]] with [[kerosene]] propellant at [[NPO Energomash]], before tackling the [[RD-170]]. So, while this later family of engines have more aggressive performance parameters and the original project (the RD-123) predates the RD-120, it was indeed the first actual design of the series development.<ref name=hendrickx2007p79 />

===RD-801 and RD-810===
While [[Yuzhnoye Design Bureau|Yuzhnoye]] propulsion experience had been mostly on [[hypergolic propellant]]s engines, like the [[RD-855]] or [[RD-861]], they were considered too toxic for modern ecological standards.<ref name=aviadvigatel /><ref name=hendrickx2007p80 /> While they still offer to develop hypergolic propulsion, like in the case of the [[RD-843]] for the [[Vega (rocket)|Vega]]'s [[AVUM]] stage or the [[Tsyklon-4]] project, for the [[Mayak (rocket family)|Mayak]] launch vehicle family a more environmentally friendly [[LOX]] and [[kerosene]] propellant was decided.<ref name=khai-aktt201301p4450 />

Not only had Yuzhnoye mastered the most complex cycle for the propellant ([[Staged combustion cycle (rocket)|oxidizer rich staged combustion cycle]]) with the [[RD-8]], but they had worked closely with [[NPO Energomash]] during the RD-120 program. The manufacturing is done at its sister company of [[Yuzhmash]] in [[Ukraine]], and the RD-120 thrust augmentation project of 2001 to 2003 had been a mixed project between the three companies.<ref name=khai-aktt201301p4450 />

On the base of this experience, a family of derivatives engines were proposed. The [[RD-805]] and [[RD-809]] are mostly modifications of the RD-8, but the [[RD-801]] and the [[RD-810]] members of the family can be considered true descendants of the RD-120.<ref name=khai-aktt201301p4450 /> One characteristic of this family is the limitation of keeping the preburner output temperature below {{convert|500|C|abbr=on}}.<ref name=khai-aktt201301p4450 />

===SCE-200===
On June 2, 2005, India and [[Ukraine]] signed the ''Framework Agreement between the Government of Ukraine and the Government of the Republic of India on Cooperation in the Peaceful Uses of Outer Space'', which would enter in force on February 15, 2006.<ref name=mfa-ukraineindialegalacts /> According to official press release on March 26, 2013 by Ukrainian Ministry of Economic Development and Trade, development of a rocket engine for Indian launch vehicles initiated in 2006 under a joint Indian-Ukrainian project named "Jasmine".<ref name=kmu-246185883 /><ref name=kmu-246186471 />

The engine blue prints supposedly transferred by Ukraine to India, have been identified as the RD-810.<ref name=b14643-ulvpropulsion /> Since the transfer specifically excluded engineering analysis methods and software, the Indians did, in fact, had to develop most technologies and engineering models to manufacture and certify the engine.<ref name=wl-07kyiv2245 /><ref name=wl-07kyiv2490 /><ref name=wl-08kyiv962 /> Given the practically identical specifications to the RD-810, and the fact that even the Indians used the Yuzhnoye renders of the engine in their presentations, it can be considered at least heavily influenced by the RD-120.<ref name=godrej-presentation />

===YF-100 and YF-115===
During the 1990s, the Chinese acquired two or three models of the RD-120, and possibly some documentation.<ref name=wl-07kyiv2491 /><ref name=sd-lm5 /> This enabled them to bootstrap their indigenous kerosene staged combustion engine program, the [[YF-100]] and [[YF-115]].<ref name=sd-lm5 /> 

As was the same case with the Indians and the RD-810, the transfer of the physical engines and blue prints only help in the development. But the development required ten years of research, requiring the mastering of 70 key technologies, the development of 50 new materials and the construction of 61 sets of engines with a combined total of more than 40,000 seconds of ignition time by 2013.<ref name=sc-acceptance />

===Derivatives comparison===

{| class="wikitable"
|+ RD-120 Technological Derivatives
|-
!Name
!RD-120
!RD-120<br />(augmented thrust)
![[RD-191]]
![[YF-100]]
![[RD-801]]
![[RD-810]]
![[SCE-200]]
|-
!AKA
|11D123 || 11D123<br />11D123M? || || || || ||
|-
!Country of Origin
|[[Soviet Union]] || Russia/[[Ukraine]] || Russia || China || Ukraine || Ukraine || India
|-
!Designer
|[[NPO Energomash]] || NPO Energomash/[[Yuzhnoye Design Bureau|Yuzhnoye]] || NPO Energomash || [[Academy of Aerospace Liquid Propulsion Technology|AALPT]] || Yuzhnoye | || Yuzhnoye || [[Liquid Propulsion Systems Centre|LPSC]]
|-
!Development years
|1976–1985 || 2001–2003 || 1999–2011 || 2000–2015|| 2005– || 2005– || 2005–
|-
!Engine Type
|colspan="7" style="text-align: center;"| [[Staged combustion cycle|Oxidizer Rich Stage Combustion]] [[upper stage]] [[Liquid-propellant rocket|liquid]] [[rocket engine]]
|-
!Propellant
|colspan="3" style="text-align: center;"| [[RP-1|RG-1]]/[[LOX]] (O/F 2.6)
|colspan="1" style="text-align: center;"| [[Kerosene]]/[[LOX]] (O/F 2.6)
|colspan="2" style="text-align: center;"| [[RP-1|RG-1]]/[[LOX]] (O/F 2.65)
| [[Kerosene|Isrosene]]/[[LOX]] (O/F 2.65)
|-
!Chamber Pressure
|{{convert|16.28|MPa|psi|abbr=on}} || {{convert|17.81|MPa|psi|abbr=on}} || {{convert|25.75|MPa|psi|abbr=on}} || {{convert|18|MPa|psi|abbr=on}} || {{convert|18|MPa|psi|abbr=on}} || {{convert|18|MPa|psi|abbr=on}} || {{convert|18|MPa|psi|abbr=on}}
|-
!Thrust (Vac)
|{{convert|833.6|kN|lbf|abbr=on}} || {{convert|912|kN|lbf|abbr=on}} || {{convert|2090|kN|lbf|abbr=on}} || {{convert|1340|kN|lbf|abbr=on}} || {{convert|1340|kN|lbf|abbr=on}} || {{convert|2105|kN|lbf|abbr=on}} || {{convert|2030|kN|lbf|abbr=on}}
|-
!Thrust (SL)
| N/A || N/A || {{convert|1920|kN|lbf|abbr=on}} || {{convert|1,200|kN|lbf|abbr=on}} || {{convert|1198|kN|lbf|abbr=on}} || {{convert|1876|kN|lbf|abbr=on}} || {{convert|1820|kN|lbf|abbr=on}}
|-
!Isp (Vac)
|{{convert|350|isp|abbr=on}} || {{convert|350|isp|abbr=on}} || {{convert|337.5|isp|abbr=on}} || {{convert|335|isp|abbr=on}} || {{convert|336|isp|abbr=on}} || {{convert|335.5|isp|abbr=on}} || {{convert|335|isp|abbr=on}}
|-
!Isp (SL)
| N/A || N/A || {{convert|311.2|isp|abbr=on}} || {{convert|300|isp|abbr=on}} || {{convert|300.7|isp|abbr=on}} || {{convert|299|isp|abbr=on}} || {{convert|299|isp|abbr=on}}
|-
!Throttle
| 70–110% || 70–110% || 27–105% || 65–100% || N/A || N/A || 65–105%
|-
!Nozzle Expansion
| 114.5 || 114.5 || 37 || 35 || N/A || N/A || N/A
|-
!Burn time
|290 seconds || 290 seconds || 325 || 155 seconds || 200 seconds || N/A || N/A
|-
!Length
|{{convert|3872|mm|in|abbr=on}} || {{convert|3872|mm|in|abbr=on}} || {{convert|3780|mm|in|abbr=on}} || N/A ||N/A  || N/A  || N/A
|-
!Diameter
|{{convert|1954|mm|in|abbr=on}} || {{convert|1954|mm|in|abbr=on}} || {{convert|2100|mm|in|abbr=on}} || {{convert|1338|mm|in|abbr=on}} || N/A  || N/A  || N/A
|-
!Weight
|{{convert|1125|kg|lb|abbr=on}} || {{convert|1125|kg|lb|abbr=on}} || {{convert|2200|kg|lb|abbr=on}} ||  N/A || {{convert|1630|kg|lb|abbr=on}} || {{convert|2800|kg|lb|abbr=on}} || {{convert|2700|kg|lb|abbr=on}}
|-
!Used on
|[[Zenit-2]] Second Stage || [[Zenit-3SL]] Second Stage || [[Angara (rocket family)|Angara]] || [[Long March 5|LM-5]], [[Long March 6|LM-6]]<br /> and [[Long March 7|LM-7]] || [[Mayak (rocket family)|Mayak]] || [[Mayak (rocket family)|Mayak]] || [[Unified Launch Vehicle|ULV]]
|-
!First Launch
|1985-04-13 || 1999-03-28 || 2014-07-09 || 2015-09-20 || N/A || N/A || N/A
|-
!Status
| Retired || In Production || In Production || In Production  || Project || Project || In Development
|-
!References
|colspan="7" style="text-align: left;"|<ref name=npoem-rd120 /><ref name=npoem-el /><ref name=k204-wiki2emash /><ref name=aviadvigatel /><ref name=yuzhmash-rd120 />
|-
|}

==See also==
*[[NPO Energomash]] – Engine designer.
*[[Yuzhmash]] – Engine manufacturer.
*[[Zenit (rocket family)|Zenit]] – Launch vehicle that used the RD-120 as second stage.
*[[YF-100]] – Chinese engine that supposedly is based on the RD-120 technology.<ref name=b14643-rd120 />
*[[RD-810]] – Ukrainian engine based on the RD-120 technology.
*[[SCE-200]] – Indian engine supposedly based on RD-120 technology.<ref name=b14643-rd120 />

== References ==
{{reflist|30em|refs=
<ref name=aviadvigatel>{{cite web |url=http://www.k204.ru/books/Aviadvigatel2.pdf |title=Двигатели 1944-2000: Аавиационные, Ракетные, Морские, Промышленные |trans-title=Aviadvigatel 19442-2000: Aviation, rocketry, naval and industry |pages=265–266 |language=ru |access-date=2015-07-25}}</ref>
<ref name=b14643-rd120>{{cite web |url=http://www.b14643.de/Spacerockets/Specials/Energomash_RD-120/index.htm |title=The family of the rocket engine Energomash RD-120 |first=Norbert |last=Brügge |publisher=B14643.de |access-date=2015-08-06 }}</ref>
<ref name=b14643-rikshadesc>{{cite web |url=http://www.b14643.de/Spacerockets_1/East_Europe_3/Riksha/Description/Text.htm |title=Riksha |first=Norbert |last=Brügge |publisher=B14643.de |access-date=2015-08-11}}</ref>
<ref name=b14643-rikshaprop>{{cite web |url=http://www.b14643.de/Spacerockets_1/East_Europe_3/Riksha/Propulsion/engines.htm |title=Propulsion Riksha |first=Norbert |last=Brügge |publisher=B14643.de |access-date=2015-08-11}}</ref>
<ref name=b14643-ulv22>{{cite web |url=http://www.b14643.de/Spacerockets_1/East_Europe_3/ULV-22/Description/Text.htm |title=ULV-22 (Edinstvo) |first=Norbert |last=Brügge |publisher=B14643.de |access-date=2015-08-11}}</ref>
<ref name=b14643-ulvpropulsion>{{cite web |url=http://www.b14643.de/Spacerockets_1/India/ULV/Propulsion/engines.htm |title=ULV Propulsion |first=Norbert |last=Brügge |publisher=B14643.de |date=2016-07-11 |access-date=2016-07-18 }}</ref>
<ref name=ea-rd120k>{{cite web |url=http://www.astronautix.com/engines/rd120k.htm |archive-url=https://web.archive.org/web/20020321080049/http://www.astronautix.com/engines/rd120k.htm |url-status=dead |archive-date=March 21, 2002 |title=RD-120K |last=Wade |first=Mark |publisher=Encyclopedia Astronautica |access-date=2015-08-11}}</ref>
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<ref name=gunter-zenit3>{{cite web |url=http://space.skyrocket.de/doc_lau/zenit-3.htm |title=Zenit-3 |publisher=Gunter's Space Page |author=Gunter Dirk Krebs |date=2015-06-28 |access-date=2015-07-25}}</ref>
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|script-title=ru:Создание семейства кислородно-керосиновых жидкостных ракетных двигателей на базе отработанных технологий для перспективных ракет-носителей гп "Кб «Южное"
|trans-title=''Creation of a family of oxygen-kerosene liquid-propellant rocket engines based on proven technologies for advanced launch vehicles of Yuzhnoye Design Bureau''  |url=http://www.khai.edu/csp/nauchportal/Arhiv/AKTT/2013/AKTT113/Degtyar.pdf |language=ru |script-journal=ru:Авиационно - космическая техника и технология
|trans-journal=Aerospace engineering and technology |publisher=National Aerospace university them. NE Zhukovsky |volume=2013 nr. 01
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<ref name=npoem-milestones>{{cite web
|url=http://www.npoenergomash.ru/encikloped/memory/
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<ref name=npoem-rd120>{{cite web
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|publisher=NPO Energomash
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<ref name=pw-a017591005>{{cite web |url=http://www.thefreelibrary.com/PRATT+%26+WHITNEY+CONDUCTS+THE+FIRST+U.S.+TEST+FIRING+OF+A+PRODUCTION...-a017591005 |title=Pratt & Whitney conducts the first U.S. test firing of a production Russian rocket engine |date=1995-10-11 |publisher=PR Newswire |access-date=2015-08-09 |archive-date=2016-03-05 |archive-url=https://web.archive.org/web/20160305160425/http://www.thefreelibrary.com/PRATT+%26+WHITNEY+CONDUCTS+THE+FIRST+U.S.+TEST+FIRING+OF+A+PRODUCTION...-a017591005 |url-status=dead }}</ref>
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<!--<ref name=wl-06kyiv4469>{{cite web |url=https://wikileaks.org/cable/2006/12/06KYIV4469.html |title=UKRAINE/NIAG 6167: PAKISTAN HEAVY WATER PURCHASE AND CHINESE INTEREST IN RD-120 ROCKET ENGINE |date=2006-12-05 |publisher=[[WikiLeaks]] |access-date=2015-08-10}}</ref>
<ref name=wl-07kyiv758>{{cite report |url=https://wikileaks.org/cable/2007/03/07KYIV758.html |title=UKRAINE: YUZHNOYE LIQUID FUEL ROCKET COOPERATION WITH CHINA |date=2007-03-30 |publisher=[[WikiLeaks]] |access-date=2015-08-10}}</ref>
<ref name=wl-07kyiv1064>{{cite report |url=https://wikileaks.org/cable/2007/05/07KYIV1064.html |title=UKRAINE/MTCR: TRAINING TO CHINA FOURTH ACADEMY AND RD-120 UPDATE |date=2007-05-07 |publisher=[[WikiLeaks]] |access-date=2015-08-10}}</ref>  -->


<ref name=wl-07kyiv2245>{{cite report |url=https://wikileaks.org/cable/2007/09/07KYIV2245.html |title=UKRAINE: APPEAL FOR USG FORBEARANCE ON INDIA SPACE PROGRAM COOPERATION |date=2007-09-07 |publisher=[[WikiLeaks]] |access-date=2015-08-10}}</ref>
<ref name=wl-07kyiv2490>{{cite report |url=https://wikileaks.org/cable/2007/09/07KYIV2490.html |title=UKRAINE: U.S. FEEDBACK ON SLV ENGINE COOPERATION WITH INDIA AND MIXER CASE |date=2007-09-28 |publisher=[[WikiLeaks]] |access-date=2015-08-10}}</ref>
<ref name=wl-07kyiv2491>{{cite report |url=https://wikileaks.org/cable/2007/09/07KYIV2491.html |title=UKRAINE/MTCR/NSG: CENTRIFUGAL CHARGING PUMPS TO CHINA/CHINESE RD-120 DEVELOPMENT |date=2007-09-28 |publisher=[[WikiLeaks]] |access-date=2015-08-10}}</ref>
<ref name=wl-08kyiv962>{{cite report |url=https://wikileaks.org/cable/2008/05/08KYIV962.html |title=UKRAINE: YUZHNOYE AND ISRO PROPOSED ROCKET COOPERATION |date=2008-05-21 |publisher=[[WikiLeaks]] |access-date=2015-08-10}}</ref>
<ref name=yuzhmash-rd120>{{cite web
|url=http://www.yuzhmash.com/production/index/rengines?id=25
|title=Liquid rocket engine RD-120
|publisher=Yuzhmash
|url-status=dead
|archive-url=https://web.archive.org/web/20150809011931/http://www.yuzhmash.com/production/index/rengines?id=25
|archive-date=9 August 2015}}</ref>
}}

==Notes==
{{reflist|group="note"|30em}}

{{Rocket engines}}
{{Russian and Soviet military designation sequences}}

==External links==
*[http://www.npoenergomash.ru/eng/dejatelnost/engines/rd120/ NPO Energia RD-120 page]
*[http://www.yuzhmash.com/production/index/rengines?id=25 Yuzhmash RD-120 page]

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