View source for RD-0110

{{short description|Soviet (later Russian) rocket engine}}
{{Use dmy dates|date=November 2024}}
{{Infobox rocket engine
| name                       = RD-0110
| image                      = RD-0110_rocket_engine.jpg
| caption                    = RD-0110 on display at the Museum of Space and Missile Technology in Saint Petersburg in September 2008
| country_of_origin          = [[Soviet Union]]{{,}}[[Russia]]
| first_date                 = 1965-10-05
| last_date                  =
| designer                   = [[Chemical Automatics Design Bureau]]
| manufacturer               = [[Voronezh Mechanical Plant]]<ref name="vmp-lre" />
| purpose                    = Upper stage engine
| associated                 = Current: [[Soyuz 2.1a]]<br>Retired: [[Molniya-M]] and most [[Soyuz (rocket family)|Soyuz]] family rockets
| predecessor                = [[RD-0108]]
| successor                  = [[RD-0124]]
| status                     = In production
| type                       = liquid
| fuel                       = [[RG-1 (propellant)|RG-1]]
| oxidiser                   = [[LOX]]
| mixture_ratio              = 2.2<ref name="ea-rd0110" />
| cycle                      = [[Gas-generator cycle (rocket)|Gas-generator]]
| combustion_chamber         = 4 main, 4 [[vernier thruster]]
| thrust(Vac)                = {{cvt|298.03|kN}}
| thrust_to_weight           = 74.36<ref name="aiaapaa-vol169" />
| chamber_pressure           = {{cvt|6.8|MPa}}
| specific_impulse_vacuum    = {{cvt|325|isp}}
| burn_time                  = 250 seconds
| length                     = {{cvt|1575|mm}}
| diameter                   = {{cvt|2240|mm}}
| dry_weight                 = {{cvt|408.5|kg}}
| used_in                    = [[Molniya-M|Molniya-M Block-I]] and on most [[Soyuz (rocket family)|Soyuz Block-I]]
| references                 = <ref name="kbkha-rd0110" /><ref name="rsw-rd0110" />
}}
The '''RD-0110''' (or '''RO-8''', '''RD-0108''', '''RD-461''' ) is a [[rocket engine]] burning [[liquid oxygen]] and [[kerosene]] in a [[Gas-generator cycle (rocket)|gas generator combustion cycle]]. It has four fixed nozzles and the output of the gas generator is directed to four secondary vernier nozzles to provide [[attitude control]] for the stage. It has an extensive flight history with its initial versions having flown more than {{time ago|10 October 1960}}.<ref name="aiaa-2005-3946" /><ref name="slr-soyuz" /><ref name="rsw-rd0110" />
== History ==
[[OKB-154]] of [[Semyon Kosberg|S.A. Kosberg]] was tasked with developing an engine for the unmanned [[Molniya-M|Molniya]] Block-I stage. Thus, the '''RD-0107''' was developed in the 1960 to 1961 period, based on the RD-0106 ([[GRAU]] Index: 8D715) engine that powered the [[SS-8 Sasin]] [[ICBM]], also designed by OKB-154. It also leveraged the experience in the field from the [[Vostok (rocket family)|Vostok]] Block-E [[RD-0105]]/[[RD-0109]] development.<ref name="kbkha-rd0110" /><ref name="rsw-rd0110" /><ref name="ea-rd0106" /><ref name="kbkha-rd0109" /> The engine had its debut flight on 10 October 1960, and the last Molniya flight was on 22 October 1967.<ref name="kbkha-rd0110" /><ref name="kosmo-ldlm" />
For the crewed carrying [[Voskhod (rocket)|Voskhod]] Block-I, a version of the engine that complied with the human rating 3K Regulations was needed. During 1963 OKB-154 developed this new version of the engine. Known with by the GRAU index 8D715P, the '''RD-0108''' kept the same characteristics and performance of the RD-0107 while fully complying with the crew rating regulations.<ref name="cosmopark-r7p9" /> This engine had its first flight on 16 November 1963, and last flew on 29 June 1976.<ref name="kbkha-rd0110" /><ref name="kosmo-ldlv" />
For the [[Molniya-M]] Block-I, OKB-154 did an improvement program that put special emphasis on the reliability of the engine. This project gave birth to the '''RD-0110'''. A particular problem observed during acceptance testing were high frequency instabilities, particularly during the start sequence. But it was solved by installing of longitudinal felt ribs on the combustion chamber.<ref name="aiaapaa-vol169" /> The development of the RD-0110 was performed in 9 months during 1963, with its inaugural flight happening in 1964.<ref name="aiaa-2005-3946" /> It is also used on the [[Soyuz (rocket family)|Soyuz]] third stage in all models until the [[RD-0124]] debut on the [[Soyuz-2 (rocket)#Soyuz 2.1b|2.1b]]. It has flown over 1350 times, and accumulated more than 336,500 s of burn time and is still flown many times per year.<ref name="aiaa-2005-3946" />
== Design ==
The RD-0110 was created in a period when KBKhA had just started to design rocket engines. After many studies, simplicity and reliability were the main drivers of the design. For this reason a single shaft integrating the LOX pump, the RG-1 pump and the turbine was chosen. To provide acceptable suction performance, the RD-0110 turbopump has a dual inlet design with back to back centrifugal impellers. This allows it to work at relatively low inlet pressures without requiring additional booster pumps. The turbine is driven by a fuel rich gas generator.<ref name="aiaa-2005-3946" /> The ignition system for both the gas generator and the combustion chamber is done by pyrotechnic devices. The engine control is handled by a regulator, a throttle and a set of valves. It can throttle between 100% and 90.5%, with the option of 107% for a short time in emergencies.<ref name="aiaapaa-vol169" />
During development, combustion instability issues were observed. The problem was found to be intimately related to the injection system design. It was finally solved by developing an optimized bi-propellant centrifugal atomizer design. During certification testing, high frequency combustion instabilities at start up were still observed. Even though the start instabilities were relatively rare at 1 in 60 to 80, and only on acceptance bench, great effort was made to eliminate the issue. Thanks to acoustic studies and modelling, a solution was found. Six combustible longitudinal felt ribs were placed at the inner surface of the combustion chamber and this solved the issue permanently.<ref name="aiaapaa-vol169" />
The RD-0110 uses fuel as coolant for the [[Regenerative cooling (rocket)|regenerative cooling]] system. As most other Soviet designs, it uses a corrugated metal construction for the cooling jackets. The thrust chamber and upper nozzle sections has the corrugated metal sandwiched between an inner and outer metal layers. The lower section of the nozzle has no external lining, exposing the corrugated jacket to save weight. All these sections use steel for construction. Given the extreme temperatures at the throat section, this part is made of copper alloy with milled channels and an external lining. A separate film cooling system is implemented though a different manifold and is injected though a circular slot upstream of the throat.<ref name="sutton-hlpre" />
== Production ==
The RD-0107/0108/0110 engines are produced in the Voronezh Mechanical Plant.<ref name="vmp-lre" /><ref name="rsw-rd0110" />
== Versions ==
Modifications to the RD-0107 design have led to production of four distinct versions of the engine:
* RD-0107 ([[GRAU]] index: 8D715K), also known as RD-461 or RO-8.<ref name="ea-rd0110" /> Used on unmanned [[Voskhod (rocket)|Voskhod]] rockets.
* RD-0108 (GRAU index: 8D715P), also known as 11D55, RD-461 or RO-8.<ref name="ea-rd0110" /> Used on the two manned Voskhod launches and the first six [[Molniya-M]] rockets.
* RD-0110 (GRAU index: 8D715P), also known as 11D55 or RD-461.<ref name="ea-rd0110" /> Used on the [[Soyuz (rocket)|Soyuz]]/[[Soyuz-L|L]]/[[Soyuz-U|U]]/[[Soyuz-U2|U2]]/[[Soyuz-FG|FG]]/[[Soyuz-2 (rocket)#Soyuz 2.1a|2.1a]] and almost all Molniya-M rockets.
* [[RD-0110R]] (GRAU index: 14D24), a heavily modified version of the engine used as [[Vernier thruster|vernier thrusters]] on the first stage of the [[Soyuz 2.1v]] rocket.
==See also==
*[[Molniya-M]] – The first LV to use the RD-0110.
*[[Soyuz (rocket family)|Soyuz rocket family]] – The most flown LV.
*[[KBKhA]] – The RD-0110 designer bureau.
*[[Voronezh Mechanical Plant]] – A space hardware manufacturer company that manufactures the RD-0110.
*[[RD-0110R]] - version of the engine modified for first stage use
==References==
{{Reflist|30em|refs=
<ref name="aiaa-2005-3946">{{Cite web |date=July 2005 |title=Turbopumps for Gas Generator and Staged Combustion Cycle Rocket Engines |url=http://www.rocket-propulsion.info/resources/articles/AIAA-2005-3946.pdf |access-date=29 May 2015 |publisher=[[AIAA]] |format=PDF}}</ref>
<ref name="aiaapaa-vol169">{{Cite book |last=Rubinsky |first=Vitaly R. |url=http://arc.aiaa.org/doi/book/10.2514/4.866371 |title=Progress in Astronautics and Aeronautics Volume 169: Liquid Rocket Engine Combustion Instability |date=1995 |publisher=[[AIAA]] |isbn=978-1-56347-183-4 |editor-last=Anderson |editor-first=William E. |pages=89–112 |chapter=Chapter 4: Combustion Instability in the RD-0110 Engine |doi=10.2514/4.866371 |access-date=30 May 2015 |editor-last2=Yang |editor-first2=Vigor |editor-link2=Vigor Yang}}</ref>
<ref name="cosmopark-r7p9">{{Cite web |title=Part 9: Launchers for an Early Circumlunar Programme |url=http://cosmopark.ru/r7/prig9.htm |url-status=live |archive-url=https://web.archive.org/web/20110925015000/http://www.cosmopark.ru/r7/prig9.htm |archive-date=25 September 2011 |publisher=Cosmopark.ru}}</ref>
<ref name="ea-rd0106">{{Cite web |title=RD-0106 |url=http://www.astronautix.com/engines/rd0106.htm |url-status=dead |archive-url=https://web.archive.org/web/20020320002530/http://www.astronautix.com/engines/rd0106.htm |archive-date=20 March 2002 |access-date=30 May 2015 |publisher=Encyclopedia Astronautica}}</ref>
<ref name="ea-rd0110">{{Cite web |title=RD-0107 |url=http://www.astronautix.com/engines/rd0107.htm |url-status=dead |archive-url=https://web.archive.org/web/20020321081012/http://www.astronautix.com/engines/rd0107.htm |archive-date=21 March 2002 |access-date=29 May 2015 |publisher=Encyclopedia Astronautica}}</ref>
<ref name="kbkha-rd0109">{{Cite web |title=RD0105. Luna (8K72) launch vehicle. RD0109. Vostok (8K72K) launch vehicle |url=http://www.kbkha.ru/?p=8&cat=8&prod=38 |url-status=dead |archive-url=https://web.archive.org/web/20111123054743/http://www.kbkha.ru/?p=8&cat=8&prod=38 |archive-date=23 November 2011 |access-date=29 May 2015 |publisher=KBKhA}}</ref>
<ref name="kbkha-rd0110">{{Cite web |title=RD0107, RD0108, RD0110. Molniya (8K78), Voskhod (8K78M), Soyuz (11A511У) launch vehicles |url=http://www.kbkha.ru/?p=8&cat=8&prod=37 |url-status=dead |archive-url=https://web.archive.org/web/20111014092851/http://www.kbkha.ru/?p=8&cat=8&prod=37 |archive-date=14 October 2011 |publisher=KBKhA}}</ref>
<ref name="kosmo-ldlm">{{Cite web |last=Pillet |first=Nicolas |title=Liste des lancements Molnia |url=http://www.kosmonavtika.com/lanceurs/soyouz/liste/8K78.html |access-date=30 May 2015 |publisher=Kosmonavtika.com |language=fr}}</ref>
<ref name="kosmo-ldlv">{{Cite web |last=Pillet |first=Nicolas |title=Liste des lancements Voskhod |url=http://www.kosmonavtika.com/lanceurs/soyouz/liste/11A57.html |access-date=30 May 2015 |publisher=Kosmonavtika.com |language=fr}}</ref>
<ref name="rsw-rd0110">{{Cite web |last=Zak |first=Anatoly |date=11 November 2020 |title=RD-0110 |url=https://russianspaceweb.com/rd0110.html |access-date=27 November 2024 |website=RussianSpaceWeb.com}}</ref>
<ref name="slr-soyuz">{{Cite web |title=R-7/Soyuz Data Sheet |url=http://www.spacelaunchreport.com/soyuz.html |url-status=dead |archive-url=https://web.archive.org/web/20100806155923/http://www.spacelaunchreport.com/soyuz.html |archive-date=6 August 2010 |publisher=Space Launch Report}}</ref>
<ref name="sutton-hlpre">{{Cite book |last=Sutton |first=George Paul |title=History of Liquid Propellant Rocket Engines |date=November 2005 |publisher=[[AIAA]] |isbn=978-1563476495 |pages=637–638}}</ref>
<ref name="vmp-lre">{{Cite web |title=Liquid Rocket Engine |url=http://vmzvrn.ru/eng/products-and-services/liquid-rocket-engine/ |url-status=dead |archive-url=https://web.archive.org/web/20150530054611/http://vmzvrn.ru/eng/products-and-services/liquid-rocket-engine/ |archive-date=30 May 2015 |publisher=Voronezh Mechanical Plant}}</ref>
}}
==External links==
{{commons category|RD-0110}}
* [http://www.kbkha.ru/ KbKhA Home Page]
*[http://vmzvrn.ru/eng/products-and-services/liquid-rocket-engine/ Voronezh Mechanical Plant] {{Webarchive|url=https://web.archive.org/web/20210306041911/http://vmzvrn.ru/eng/products-and-services/liquid-rocket-engine/ |date=6 March 2021 }}
* [http://en.samspace.ru/ RSC Progress Home Page]
* [https://web.archive.org/web/20070715063836/http://www.astronautix.com/engines/rd0110.htm РД-0110 в энциклопедии Astronautix.com.]
{{Rocket engines}}
[[Category:Rocket engines of Russia]]
[[Category:Rocket engines of the Soviet Union]]
[[Category:Rocket engines using kerosene propellant]]
[[Category:Rocket engines using the gas-generator cycle]]
[[Category:KBKhA rocket engines]]