# RD-253

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Soviet engine design used on the first stage of Proton rockets

RD-253 Mock-up of a RD-275 rocket motor at the Paris Air Show in 2013 Country of origin Soviet Union Russia First flight RD-253: 1965 RD-275: 1995 RD-275М: 2007 Designer NPO Energomash, Valentin Glushko Manufacturer Proton-PM Application First stage booster Associated LV Proton Successor RD-254, RD-256, RD-275, RD-275М Status Operational Liquid-fuel engine Propellant N2O4 / UDMH Mixture ratio 2.67 Cycle Staged combustion Configuration Chamber 1 Nozzle ratio 26.2 Performance Thrust, vacuum RD-253: 1,630 kN (370,000 lbf) RD-275: 1,750 kN (390,000 lbf) RD-275М: 1,832 kN (412,000 lbf) Thrust, sea-level RD-253: 1,470 kN (330,000 lbf) RD-275: 1,590 kN (360,000 lbf) RD-275М: 1,671 kN (376,000 lbf) Thrust-to-weight ratio 156.2 Chamber pressure RD-253: 14.7 MPa (2,130 psi; 147 bar) RD-275: 15.7 MPa (2,280 psi; 157 bar) RD-275M: 16.5 MPa (2,390 psi; 165 bar) 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 Gimbal range 7.5°, single plane Dimensions Length 3 m (9.8 ft) Diameter 1.5 m (4 ft 11 in) Dry mass RD-253: 1,080 kg (2,380 lb) RD-275: 1,070 kg (2,360 lb) RD-275M: 1,070 kg (2,360 lb) References References [1][2][3][4][5][6][7]

The **RD-253** ([Russian](/source/Russian_language): Ракетный Двигатель-253, [romanized](/source/Romanization_of_Russian): *Raketnyy Dvigatel-253*, [lit.](/source/Literal_translation) 'Rocket Engine 253') and its later variants, the **RD-275** and **RD-275M**, are [liquid-propellant rocket](/source/Liquid-propellant_rocket) [engines](/source/Rocket_engine) developed in the [Soviet Union](/source/Soviet_Union) by [Energomash](/source/NPO_Energomash). The engines are used on the first stage of the [Proton](/source/Proton_(rocket)) launch vehicle and use an oxidizer-rich [staged combustion](/source/Staged_combustion_cycle_(rocket)) cycle to power the turbopumps. The engine burns a [hypergolic](/source/Hypergolic_propellant) mixture of [unsymmetrical dimethylhydrazine](/source/Unsymmetrical_dimethylhydrazine) (UDMH) fuel with [dinitrogen tetroxide](/source/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](/source/Valentin_Glushko) and finished in 1963. The RD-253 uses an [oxidiser-rich staged combustion](/source/Staged_combustion_cycle_(rocket)#Oxidizer-rich_staged_combustion) cycle. It was used for the first time in July 1965, when six engines powered the first stage of the [Proton](/source/Proton_(rocket_family)) rocket. Development and production of RD-253 was a qualitative leap forward for rocketry of that time by achieving high levels of [thrust](/source/Thrust), [specific impulse](/source/Specific_impulse) and pressure in the [combustion chamber](/source/Combustion_chamber). This engine is one of the most reliable engines in the [USSR](/source/USSR) and modern [Russia](/source/Russia).

As the first stage of the [Proton-K](/source/Proton-K) rocket used six RD-253 engines, the system played a pivotal role in Russian [space missions](/source/Space_mission) when this rocket was chosen as a carrier, including the following programs: ["Luna"](/source/Luna_programme), "[Venera](/source/Venera)", ["Mars probe"](/source/Mars_probe_program), crewed [orbital stations](/source/Orbital_station) ["Salyut"](/source/Salyut_program), "[Mir](/source/Mir)", and it launched several principal modules for [ISS](/source/ISS). It was widely used for the launches of heavy satellites.[1][5] The last RD-253 rocket engine was used on a Proton-K rocket and launched on March 30, 2012.[6]

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.[8] 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](/source/Proton_(rocket)) rocket are held by [Energomash](/source/NPO_Energomash) which produces it in [Perm](/source/Perm%2C_Russia), [Russia](/source/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](/source/Combustion_chamber) and enabled an increase of [payload](/source/Payload_(air_and_space_craft)) mass to [geostationary orbit (GEO)](/source/Geostationary_orbit) up to more than 6,000 kg (13,000 lb). The successful maiden flight of a [Proton](/source/Proton_(rocket)) rocket with the new engine was completed in 1995.

[Energomash](/source/NPO_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 150 kg (330 lb) more payload to [GEO](/source/Geostationary_orbit).[1]

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[s](/source/Second). In the middle of 2005, this engine went into production by government commission. The first launch of a [Proton-M](/source/Proton-M) with 14D14M engines was launched on July 7, 2007.[1]

The final version RD-275M is sometimes designated as RD-276, but through 2009 the name RD-275M (14D14M) was more common.[1][4] Some sources[*[which?](https://en.wikipedia.org/wiki/Wikipedia:Avoid_weasel_words)*] points out the cost of production per engine as much as 1.5 million [USD](/source/USD) and sometimes calls some lower figures around 1 million [USD](/source/USD) per unit.[*[citation needed](https://en.wikipedia.org/wiki/Wikipedia:Citation_needed)*]

## Versions

During the years there have been many versions of this engine:

- **RD-220**: Initial proposal for the [N-1](/source/N1_(rocket)) first stage.[9]

- **RD-221**: Initial proposal for the [N-1](/source/N1_(rocket)) second stage.[9]

- **RD-222** ([GRAU](/source/GRAU) Index **11D41**): Development program for the [N-1](/source/N1_(rocket)) first stage.[9]

- **RD-223** ([GRAU](/source/GRAU) Index **11D42**): Development program for the [N-1](/source/N1_(rocket)) second stage.[9]

- **RD-253** ([GRAU](/source/GRAU) Index **11D43**): Serial production version for the [Proton](/source/Proton-K) (8K62) first stage. Was proposed for the [N-1](/source/N1_(rocket)) first stage.

- **RD-253F** ([GRAU](/source/GRAU) Index **11D43F**): Project for [R-36M](/source/R-36_(missile)#R-36M_(SS-18)_variants) (15А14) first stage.[9]

- **RD-254** ([GRAU](/source/GRAU) Index **11D44**): Project for [UR-700](/source/Universal_Rocket#UR-700) third stage and for [Proton](/source/Proton-K) and [N-1](/source/N1_(rocket)) second stages, it was a RD-253 high-altitude version.

- **RD-275** ([GRAU](/source/GRAU) Index **14D14**): Serial production for [Proton-M](/source/Proton-M) first stage. RD-253 with increased thrust by 8%.[9]

- **RD-276** ([GRAU](/source/GRAU) Index **14D14М**): Serial production for [Proton-M](/source/Proton-M) first stage. Sometimes previously called RD-275M. Improved RD-275.[9]

RD-253 Family of Engines[9] Engine RD-220 RD-221 RD-222 (11D41) RD-223 (11D42) RD-253 (11D413) RD-253F (11D413F) RD-254 (11D44) RD-275 (14D14) RD-275M (RD-276, 14D14M)[4] Development 1960 1960-1961 1962-1966 1966-1967 1961-1963 1987-1993 2001-2005 Combustion Chamber Pressure 14.7 MPa (2,130 psi) 16.9 MPa (2,450 psi) 14.7 MPa (2,130 psi) 15.7 MPa (2,280 psi) 16.5 MPa (2,390 psi) Thrust (Vacuum) 1,074 kN (241,000 lbf) 1,120 kN (250,000 lbf) 1,634 kN (367,000 lbf) 1,700 kN (380,000 lbf) 1,635 kN (368,000 lbf) 1,870 kN (420,000 lbf) 1,720 kN (390,000 lbf) 1,750 kN (390,000 lbf) 1,832 kN (412,000 lbf) Thrust (Sea Level) 947 kN (213,000 lbf) N/A 1,471 kN (331,000 lbf) N/A 1,474 kN (331,000 lbf) 1,720 kN (390,000 lbf) N/A 1,590 kN (360,000 lbf) 1,671 kN (376,000 lbf) Specific Impulse (Vacuum) 306 s (3.00 km/s) 318 s (3.12 km/s) 302 s (2.96 km/s) 314 s (3.08 km/s) 316 s (3.10 km/s) 317 s (3.11 km/s) 328 s (3.22 km/s) 316 s (3.10 km/s) 315.8 s (3.097 km/s) Specific Impulse (Sea Level) 270 s (2.6 km/s) N/A 272 s (2.67 km/s) N/A 285 s (2.79 km/s) 290 s (2.8 km/s) N/A 287 s (2.81 km/s) 288 s (2.82 km/s) Height 2,600 mm (100 in) 4,200 mm (170 in) 3,470 mm (137 in) 5,050 mm (199 in) 3,000 mm (120 in) 2,700 mm (110 in) 4,000 mm (160 in) 3,050 mm (120 in) 3,050 mm (120 in) Diameter 1,300 mm (51 in) 2,400 mm (94 in) 1,460 mm (57 in) 2,530 mm (100 in) 1,500 mm (59 in) 1,490 mm (59 in) 2,600 mm (100 in) 1,500 mm (59 in) 1,500 mm (59 in) Intended Use N-1 first stage N-1 second stage N-1 first stage N-1 second stage Proton (8K62) first stage R-36M (15А14) first stage UR-700 third stage, Proton and N-1 second stages Proton-M first stage Proton-M first stage Status Project (Abandoned) Retired Project (Abandoned) Retired In Production

## See also

- [Proton](/source/Proton_(rocket)) - uses RD-275

- [Rocket engine](/source/Rocket_engine)

### References

1. ^ [***a***](#cite_ref-npoem-rd253_1-0) [***b***](#cite_ref-npoem-rd253_1-1) [***c***](#cite_ref-npoem-rd253_1-2) [***d***](#cite_ref-npoem-rd253_1-3) [***e***](#cite_ref-npoem-rd253_1-4) ["RD-253"](https://web.archive.org/web/20150405185423/http://www.npoenergomash.ru/eng/dejatelnost/engines/rd253/). [NPO Energomash](/source/NPO_Energomash). Archived from [the original](http://www.npoenergomash.ru/eng/dejatelnost/engines/rd253/) on 5 April 2015.

1. **[^](#cite_ref-ea-rd211d48_2-0)** ["RD-253-11D48"](https://web.archive.org/web/20160304061218/http://www.astronautix.com/engines/rd211d48.htm). *Encyclopedia Astronautica*. Archived from [the original](http://www.astronautix.com/engines/rd211d48.htm) on 2016-03-04. Retrieved 2015-07-07.

1. **[^](#cite_ref-ea-rd253_3-0)** ["RD-253"](https://web.archive.org/web/20150824113758/http://www.astronautix.com/engines/rd253.htm). *Encyclopedia Astronautica*. Archived from [the original](http://www.astronautix.com/engines/rd253.htm) on 2015-08-24. Retrieved 2015-07-07.

1. ^ [***a***](#cite_ref-protonpm-rd276_4-0) [***b***](#cite_ref-protonpm-rd276_4-1) [***c***](#cite_ref-protonpm-rd276_4-2) ["Liquid rocket engine RD-276"](https://web.archive.org/web/20220115224122/https://protonpm.ru/creator/production/produce_and_services/pg1/84/). Proton-PM. Archived from [the original](http://www.protonpm.ru/creator/production/produce_and_services/pg1/84/) on 15 January 2022. Retrieved 6 July 2015.

1. ^ [***a***](#cite_ref-ea-protonk_5-0) [***b***](#cite_ref-ea-protonk_5-1) ["Proton-K"](https://web.archive.org/web/20100822083221/http://www.astronautix.com/lvs/protonk.htm). *Encyclopedia Astronautica*. Archived from [the original](http://www.astronautix.com/lvs/protonk.htm) on August 22, 2010. Retrieved 2015-07-07.

1. ^ [***a***](#cite_ref-rsw-protonhist_6-0) [***b***](#cite_ref-rsw-protonhist_6-1) Zak, Anatoly. ["Proton History"](http://www.russianspaceweb.com/proton_history.html). *RussianSpaceWeb*. Retrieved 2015-07-07.

1. **[^](#cite_ref-rsw-rd353_7-0)** Zak, Anatoly. ["2015-07-07"](http://www.russianspaceweb.com/rd253.html). *RussianSpaceWeb*. Retrieved 2015-07-07.

1. **[^](#cite_ref-lprd-rd253_8-0)** ["RD-253 (11D43) and RD-275 (14D14)"](http://www.lpre.de/energomash/RD-253/index.htm) (in Russian). Retrieved 2015-07-07.

1. ^ [***a***](#cite_ref-npoem-el_9-0) [***b***](#cite_ref-npoem-el_9-1) [***c***](#cite_ref-npoem-el_9-2) [***d***](#cite_ref-npoem-el_9-3) [***e***](#cite_ref-npoem-el_9-4) [***f***](#cite_ref-npoem-el_9-5) [***g***](#cite_ref-npoem-el_9-6) [***h***](#cite_ref-npoem-el_9-7) ["NPO Energomash list of engines"](https://web.archive.org/web/20141107202512/http://www.npoenergomash.ru/netcat_files/File/Table_of_Engines.docx). [NPO Energomash](/source/NPO_Energomash). Archived from [the original](http://www.npoenergomash.ru/netcat_files/File/Table_of_Engines.docx) on 7 November 2014.

v t e Rocket engines and solid motors for orbital launch vehicles Comparison of orbital rocket engines Liquid fuel Cryogenic Hydrolox (LH2 / LOX) China YF-73 YF-75 YF-75D YF-77 YF-79 YF-90 Europe HM7B Vinci Vulcain India CE-7.5 CE-20 Japan LE-5 LE-7 LE-9 Russia KVD-1 (RD-56) RD-0120 RD-0146 United States BE-3U BE-7 J-2 RL10 RS-2200 RS-25 RS-68 RS-83 TR-106 XRS-2200 Methalox (CH4 / LOX) China BF-20 Lingyun Longyun TQ-11 TQ-12 TQ-15A YF-209 YF-215 United States BE-4 Raptor Archimedes Aeon 1 Aeon R Russia RD-0169 Europe Prometheus M10 Semi- cryogenic Kerolox (RP-1 / LOX) China TH-11 TH-12 YF-100 YF-102 YF-115 YF-130 Welkin India SCE-200 Russia NK-15 NK-33, 44 RD-58 RD-0105, 0109 RD-0107, 0108, 0110 RD-0110R RD-0124 RD-107, 108, 117, 118 RD-120 RD-170, 171 RD-180 RD-191, 151, 181 RD-193 S1.5400 Spain TEPREL Ukraine RD-8 RD-801 RD-810 United States AR1 F-1 H-1 Kestrel LR-79 LR89 LR105 LR70-NA , S-3D Merlin Miranda RS-27 RS-27A RS-56 RS-84 S-3D Rutherford TR-107 XLR50 Storable Hypergolic (Aerozine, UH 25, MMH, or UDMH / N2O4, MON, or HNO3) China YF-1, 2, 3 YF-20, 21, 22, 24, 25 YF-23 YF-40 YF-50D Europe Aestus Astris Vexin Viking India PS4 Vikas Israel LK-4 North Korea Paektusan LRE along other LREs Russia 17D61 RD-0202 to 0206, 0208 to 0213 RD-0207, 0214 RD-0216, 0217, 0235 RD-0233, 0234 RD-0236 RD-0237 RD-0243 to 0245 RD-0255 to 0257 RD-215 to 219 RD-250 to 252, 261, 262 RD-253, 275 RD-263, 268, 273 RD-270 S5.92 S5.98M Ukraine RD-843 RD-854, 861 RD-855 RD-856 RD-864, 869 United States AJ10 LR-87 LR-91 RS-88* TR-201 VTR-10 XLR81* Other Russia RD-0410 RD-109, 119 RD-211 to 214 UK Gamma United States Curie Kiwi A, Kiwi B NERVA RS-88* XLR81* Solid fuel China FG-02 FG-36 FG-46 FG-47 SpaB-65 SpaB-140C Europe Mage 1 P-4 P-6 PAP P80 P120C P230 Topaze Waxwing Zefiro 9 Zefiro 23 Zefiro 40 India S7 S9 S12 S139 S200 Iran Salman Rafe Israel LK-1 RSA-3 Japan KM-V1 KM-V2b M-14 M-24 M-34 M-34c SRB-A United States AJ-60A Algol Castor 30 GEM Orbus-6 Orbus-21 Orion Space Shuttle SRB Star 37 Star 48 UA120 SRMU X-248 X-254 * Different versions of the engine use different propellant combinations Engines in italics are/were under development

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Adapted from the Wikipedia article [RD-253](https://en.wikipedia.org/wiki/RD-253) by Wikipedia contributors ([contributor history](https://en.wikipedia.org/wiki/RD-253?action=history)). Available under [Creative Commons Attribution-ShareAlike 4.0 International](https://creativecommons.org/licenses/by-sa/4.0/). Changes may have been made.