View source for 11D428

{{Infobox rocket engine
|name            =11D428A-16
|image           =
|image_size      =
|caption         =
|country_of_origin=[[Russia]]
|date            =1993–1997
|first_date      =1997-10-05 ([[Progress M-36]])
|last_date       =
|designer        =[[Federal State Unitary Enterprise Research and Development Institute of Mechanical Engineering|NIIMash]]
|manufacturer    =
|purpose         =[[Reaction control system|RCS]] thruster
|associated      =
|predecessor     =11D428A
|successor       =11D428AF-16
|status          =In Production
|type            =liquid
|fuel            =[[Unsymmetrical dimethylhydrazine|UDMH]]
|oxidiser        =[[Dinitrogen tetroxide|N<sub>2</sub>O<sub>4</sub>]]
|mixture_ratio   =1.85±0.15
|cycle           =[[Pressure-fed engine|pressure fed]]
|pumps           =
|description     =
|combustion_chamber=1
|nozzle_ratio    =
|thrust          =
|thrust_at_altitude=
|thrust(Vac)     ={{convert|129.16|N|lbf|abbr=on}}
|thrust(SL)      =
|thrust_to_weight=
|chamber_pressure={{convert|0.88|MPa|psi|abbr=on}}
|specific_impulse=
|specific_impulse_vacuum={{convert|291|isp|abbr=on}}
|specific_impulse_sea_level=
|total_impulse   =
|burn_time       =
|restarts        =500,000
|gimbal          =<!--gimbal range in °, leave blank if none-->
|capacity        =
|dimensions      =
|length          =
|diameter        =
|dry_weight      ={{convert|1.5|kg|lb|abbr=on}}
|used_in         =[[Soyuz (spacecraft)|Soyuz]] since [[Soyuz TM-28]] and [[Progress (spacecraft)|Progress]] since [[Progress M-36]]
|references      =<ref name=aviadvigatel /><ref name=kn-soyuzukdu /><ref name=niimash-11d428a16 />
|notes           =
}}
The '''11D428A-16''' (manufacturer's name '''RDMT-135M''') is a [[Liquid-propellant rocket|liquid]] [[Pressure-fed engine|pressure-fed]] [[rocket engine]] burning [[Dinitrogen tetroxide|N<sub>2</sub>O<sub>4</sub>]]/[[Unsymmetrical dimethylhydrazine|UDMH]] with an [[Rocket propellant#Mixture ratio|O/F]] of 1.85. It is used for crew-rated [[spacecraft propulsion]] applications. It is currently used in the [[KTDU-80]] spacecraft propulsion module. The previous version, the '''11D428A''' (manufacturer's name '''RDMT-135''') is still used as the [[reaction control system]] thrusters of the [[Zvezda (ISS module)|Zvezda]] [[International Space Station|ISS]] module.
The 11D428A-16 generates {{convert|129.16|N|lbf|abbr=on}} of thrust with a chamber pressure of {{convert|0.88|MPa|psi|abbr=on}} and achieves a [[specific impulse]] of {{convert|291|isp|abbr=on}}. It is rated for 500,000 starts with a certified ignition time of 0.03 seconds to 2000 seconds. Each unit weights {{convert|1.5|kg|lb|abbr=on}}.
==Versions==
This engine has been used with certain variations in the [[Human spaceflight|crewed]] [[Russian space program]] since the [[Salyut 6]] in [[Soviet space program|Soviet]] times. The three main versions are:<ref name=niimash-history />
* '''11D428''': Delivered in 1970 for use in [[Salyut 1]].
* '''11D428M''': Version developed for the [[Yantar-2K]] platform. It reached space on the first launch, [[Kosmos 697]] on August 6, 1974.
* '''11D428A''' (AKA '''RDMT-135'''): Version developed for the [[Soyuz 7K-S]], it flew on [[Kosmos 670]], [[Kosmos 772]] and [[Kosmos 869]]. Later used on the [[KTDU-426]].<ref name=ea-rdmt135 />
* '''11D428A-10''': Thruster used on the [[Zvezda (ISS module)|Zvezda ISS Module]]. Originally developed for the [[Mir Core Module]].
* '''11D428A-14''': Thruster used on the Zvezda ISS module.
* '''11D428A-16''' (AKA '''RDMT-135M'''): Improved specific impulse version. Used on the [[KTDU-80]] since [[Soyuz TM-28]].<ref name=rkke-som />
* '''11D428AF-16''':Thruster version developed for the [[Fobos-Grunt]] planetary sample mission.
{| class="wikitable mw-collapsible"
|-
! Engine !! 11D428A !! 11D428A-16 !! 11D428AF-16
|-
!Development
| 1968–1974 || 1968–1977 || 1993–1997
|-
! Engine Type
| colspan="3" style="text-align: center;" | [[Liquid-propellant rocket|Liquid]] [[Pressure-fed engine|pressure-fed]] [[rocket engine]]
|-
! Propellant
| colspan="3" style="text-align: center;" | [[Dinitrogen tetroxide|N<sub>2</sub>O<sub>4</sub>]]/[[Unsymmetrical dimethylhydrazine|UDMH]] with 1.85 O/F ratio
|-
!Thrust
| {{convert|130.5|N|lbf|abbr=on}} || {{convert|129.16|N|lbf|abbr=on}} || {{convert|123.5|N|lbf|abbr=on}}
|-
![[Specific impulse|isp]]
| 1:56 Exp. Nozzle:{{convert|290|isp|abbr=on}}<br />1:150 Exp. Nozzle:{{convert|302|isp|abbr=on}} || {{convert|291|isp|abbr=on}} || {{convert|306.2|isp|abbr=on}}
|-
!Nominal Inlet Pressure
| {{convert|1.77|MPa|psi|abbr=on}} || {{convert|1.76|MPa|psi|abbr=on}} || {{convert|1.47|MPa|psi|abbr=on}}
|-
!Nozzle
| 1 || 1 || 1
|-
!Burn time
| 570s || 2700s || 50,000s
|-
!Ignitions
| colspan="3" style="text-align: center;" | 500,000
|-
!Ignition time
| colspan="3" style="text-align: center;" | 0.03 to 2000s
|-
!Mass
| {{convert|1.2|kg|lb|abbr=on}} || {{convert|1.5|kg|lb|abbr=on}} || {{convert|1.9|kg|lb|abbr=on}}
|-
!Length
| {{convert|274|mm|in|abbr=on}} || {{convert|289.5|mm|in|abbr=on}} || {{convert|372|mm|in|abbr=on}}
|-
!Diameter
| {{convert|98|mm|in|abbr=on}} || <!--{{convert||mm|in|abbr=on}}--> || {{convert|157.4|mm|in|abbr=on}}
|-
!Uses
| [[Soyuz 7K-S]], [[Soyuz-T]] and [[Soyuz-TM]] || [[Soyuz-TMA]], [[Salyut-6]], [[Salyut-7]], [[Mir Core Module]], [[Zvezda (ISS module)|Zvezda]] || [[Fobos-Grunt]]
|-
! References
| colspan="3" style="text-align: left;" | <ref name=aviadvigatel /><ref name=niimash-11d428a16 /><ref name=niimash-11d428af16 /><ref name=lprd-niimash /><ref name=ea-rdmt100 />
|-
|}
==See also==
*[[KB KhIMMASH]]
*[[KTDU-35]]
*[[KTDU-80]]
*[[Soyuz-T]]
*[[Soyuz-TM]]
==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=75–81 |format=PDF |language=Russian |access-date=2015-07-25}}</ref>
<ref name=ea-rdmt100>{{cite web |url=http://www.astronautix.com/engines/rdmt100.htm |title=RDMT-100 |publisher=Encyclopedia Astronautica |access-date=2015-07-30 |url-status=dead |archive-url=https://web.archive.org/web/20150824113726/http://www.astronautix.com/engines/rdmt100.htm |archive-date=2015-08-24 }}</ref>
<ref name=ea-rdmt135>{{cite web |url=http://www.astronautix.com/engines/rdmt135.htm |title=RDMT-135 |publisher=Encyclopedia Astronautica |access-date=2015-07-30 |url-status=dead |archive-url=https://web.archive.org/web/20150824113527/http://www.astronautix.com/engines/rdmt135.htm |archive-date=2015-08-24 }}</ref>
<ref name=kn-soyuzukdu>{{cite web |url=http://www.kosmonavtika.com/vaisseaux/soyouz/tech/kdu/kdu.html |title=Le système de propulsion du vaisseau Soyouz |trans-title=The propulsion system of the Soyuz spacecraft |first1=Nicolas |last1=Pillet |publisher=Kosmonavtika.com |language=French |access-date=2015-07-14}}</ref>
<ref name=lprd-niimash>{{cite web |url=http://www.rocket-propulsion.info/resources/articles/LTREs_all.pdf |title=Серийный двухкомпонентный ракетный двигатель малой тяги 11Д428А |trans-title=Bipropellant thruster 11D428A |publisher=[[NIIMash]] |language=Russian |format=PDF |access-date=2015-07-25}}</ref>
<ref name=niimash-history>{{cite web |url=http://niimashspace.ru/index.php/2010-07-16-10-53-23/hiistory |title=История |trans-title=History |publisher=[[NIIMash]] |language=Russian |access-date=2015-07-30}}</ref>
<ref name=niimash-11d428a16>{{cite web |url=http://niimashspace.ru/index.php/produce/rkt/33-rdmt/7-11428-16 |title=Двухкомпонентный ракетный двигатель малой тяги 11Д428А-16 |trans-title=Bipropellant thruster 11D428A-16 |publisher=[[NIIMash]] |language=Russian |access-date=2015-07-30 |archive-url=https://web.archive.org/web/20151126065356/http://niimashspace.ru/index.php/produce/rkt/33-rdmt/7-11428-16 |archive-date=2015-11-26 |url-status=dead }}</ref>
<ref name=niimash-11d428af16>{{cite web |url=http://niimashspace.ru/index.php/produce/rkt/33-rdmt/8-11428-161 |title=Двухкомпонентный ракетный двигатель малой тяги 11Д428АФ-16 |trans-title=Bipropellant thruster 11D428AF-16 |publisher=[[NIIMash]] |language=Russian |access-date=2015-07-30 |archive-url=https://web.archive.org/web/20151126065817/http://niimashspace.ru/index.php/produce/rkt/33-rdmt/8-11428-161 |archive-date=2015-11-26 |url-status=dead }}</ref>
<ref name="rkke-som">{{cite book |chapter=3.17. Комбинированная Двигательная Установка (КДУ) (Combined Propulsion System) |pages=122–129 |last1=Malikov |first1=A. |last2=Zhuk |first2=E. |title=Soyuz Crew Operations Manual (SoyCOM) (ROP-19) (Final) |url=https://www.planet4589.org/space/articles/pao/CrewManual1999.pdf |publisher=[[Yuri Gagarin Cosmonaut Training Center|Yu.A. Gagarin Cosmonautís Training Center]] |date=June 1999 |archive-url=https://web.archive.org/web/20230816231017/https://www.planet4589.org/space/articles/pao/CrewManual1999.pdf |archive-date=16 August 2023 |url-status=live }}</ref>
}}
==External links==
* [http://kbhmisaeva.ru/main.php?id=53 KB KhIMMASH Official Page (in Russian)] {{Webarchive|url=https://web.archive.org/web/20160320132115/http://kbhmisaeva.ru/main.php?id=53 |date=2016-03-20 }}
{{Orbital spacecraft rocket engines}}
[[Category:Rocket engines of Russia]]
[[Category:Rocket engines of the Soviet Union]]
[[Category:Rocket engines using hypergolic propellant]]
[[Category:Rocket engines using the pressure-fed cycle]]
[[Category:NIIMash rocket engines]]