RD-58

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title: "RD-58" type: doc version: 1 created: 2026-02-28 author: "Wikipedia contributors" status: active scope: public tags: ["rocket-engines-of-the-soviet-union", "rocket-engines-of-russia", "rocket-engines-using-kerosene-propellant", "rocket-engines-using-the-staged-combustion-cycle", "energia-rocket-engines"] description: "Rocket engine" topic_path: "geography/russia" source: "https://en.wikipedia.org/wiki/RD-58" license: "CC BY-SA 4.0" wikipedia_page_id: 0 wikipedia_revision_id: 0

::summary Rocket engine ::

::data[format=table title="Infobox rocket engine"]

Field	Value
name	RD-58M
image	17Д12.jpg
country_of_origin	USSR
first_date	1967
designer	OKB-1, V. M. Melnikov
manufacturer	Voronezh Mechanical Plant
purpose	Upper Stage
associated	N1, Proton-K, Proton-M, Zenit
predecessor	S1.5400
status	In Production
type	liquid
oxidiser	LOX
fuel	RG-1
cycle	Oxidizer-rich staged combustion
combustion_chamber	1
thrust(Vac)	79.46 kN
specific_impulse_vacuum	353 s
burn_time	up to 600 s
dry_weight	300 kg
used_in	Block D
references
::

|name = RD-58M |image =17Д12.jpg |image_size = |caption = |country_of_origin= USSR |date = |first_date = 1967 |last_date = |designer =OKB-1, V. M. Melnikov |manufacturer =Voronezh Mechanical Plant |purpose =Upper Stage |associated =N1, Proton-K, Proton-M, Zenit |predecessor =S1.5400 |successor = |status =In Production |type = liquid |oxidiser = LOX |fuel = RG-1 |mixture_ratio = |cycle =Oxidizer-rich staged combustion |pumps = |description = |combustion_chamber=1 |nozzle_ratio = |thrust = |thrust_at_altitude= |thrust(Vac) = 79.46 kN |thrust(SL) = |thrust_to_weight= |chamber_pressure= |specific_impulse= |specific_impulse_vacuum= 353 s |specific_impulse_sea_level= |total_impulse = |burn_time = up to 600 s |capacity =

|dimensions = |length = |diameter = |dry_weight = 300 kg

|used_in = Block D

|references = |notes = The RD-58 (, GRAU index: 11D58) is a rocket engine, developed in the 1960s by OKB-1, now RKK Energia. The project was managed by Mikhail Melnikov, and it was based on the previous S1.5400 engine, which was the first staged combustion engine in the world. The engine was initially created to power the Blok D stage of the Soviet Union's abortive N1 rocket. Derivatives of this stage are now used as upper stages on some Proton and Zenit rockets. An alternative version of the RD-58 chamber, featuring a shorter nozzle, was used as the N1's roll-control engine.

The RD-58 uses liquid oxygen as the oxidizer and RG-1 as fuel in an oxidizer-rich staged combustion cycle. It features a single gimbaled chamber, radial centrifugal pumps with auxiliary booster pumps, and an oxygen-rich preburner. Recent modifications include a lightweight carbon-composite nozzle extender developed by NPO Iskra.

The Buran spacecraft used two of an evolution of the RD-58M, called 17D12, as its main orbital correction engines. Instead of RG-1, it burned Syntin, and could be ignited 15 times. It is assumed that it was the base for the RD-58S, which had practically the same specifications and powered the Blok DM-2M. But the manufacturer states that the engine is compatible with both propellants.

The current version of the engine is the RD-58M (manufacturer designation 11D58M), which has slightly reduced thrust, but increased isp. An even newer version is under development and is known as the RD-58MF (manufacturer designation 11D58MF). It will reduce thrust to 49.03 kN to keep the same length but increase expansion ratio to 500:1. This will enable it to gain 20s of isp (to an expected 372s). It will eventually fly on the Blok DM-03. This new version of the engine will be built in the Krasnoyarsk Machine-Building Plant. During a November 2014 interview, Vladimir Kolmykov, the Deputy General Director of the Chemical Division of Krasnoyarsk Machine-Building Plant, stated that the production of Block-DM was suspended during that year, but work on the stage and development of the RD-58MF will resume during 2015.

Versions

This engine has had many versions through the years:

• RD-58 (GRAU Index 11D58): Original version developed for the Blok D of the N1 (rocket).
• RD-58M (GRAU Index 11D58M): Improved version developed for the Proton Blok D.
• RD-58M (Carbon-carbon nozzle): Version of the RD-58M that replaces the regeneratively cooled nozzle for a carbon-carbon extension manufactured by NPO Iskra. Used on Zenit-3SL's Blok DM-SL since June 10, 2003 on the Thuraya 2 launch.
• RD-58MF (GRAU Index 11D58MF): Reduced thrust and increased specific impulse version expected to fly on the Proton and Zenit Blok DM-03. Will probably also use a carbon-carbon nozzle extension.
• RD-58S (GRAU Index 11D58S): Version designed to use Syntin synthetic propellant rather than RG-1. Used on the Blok DM-2M. Probably developed based on the 17D12.
• RD-58Z (GRAU Index 11D58Z): Version adapted to the Zenit Blok DM-SL.
• 17D12: Orbital maneuvering engines (DOM) of the Buran propulsion system 17D11, burned Syntin/LOX.

::data[format=table title="RD-58 Family of Engines"] | Name | RD-58 | RD-58M | RD-58M (Carbon Composite Nozzle) | RD-58S | RD-58Z | RD-58MF | 17D12 | Index | Development years | Engine Type | Propellant | O/F | Chamber Pressure | Thrust (Vac) | Isp (Vac) | Nozzle Expansion | Ignitions | Burntime | Length | Diameter | Weight | Used on | First Launch | Status | References | |---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---| | 11D58 | 11D58M | | 11D58S | 11D58Z | 11D58MF | | | | | | | | | | | | | | | | | | | | | | 1964–1968 | 1970–1974 | 2000–2004 | 1986–1995 | 1981–1990 | 2002–2009 | 1981–1987 | | | | | | | | | | | | | | | | | | | | | Oxidizer-rich stage combustion upper stage liquid rocket engine | Orbital correction liquid rocket engine | | | | | | | | | | | | | | | | | | | | | | | | | | RG-1/LOX | RG-1/LOX | RG-1/LOX | Syntin/LOX | RG-1/LOX | RG-1/LOX | Syntin/LOX | | | | | | | | | | | | | | | | | | | | | 2.48 | 2.48 | 2.82 | ? | 2.6 | 2.82 | ? | | | | | | | | | | | | | | | | | | | | | 7.8 MPa | 7.75 MPa | 7.9 MPa | 7.94 MPa | 7.8 MPa | 7.9 MPa | 7.94 MPa | | | | | | | | | | | | | | | | | | | | | 83.4 kN | 83.4 kN | 85 kN | 86.3 kN | 71 kN | 49.03 kN | 86.24 kN | | | | | | | | | | | | | | | | | | | | | 349 isp | 356 isp | 361 isp | 361 isp | 361 isp | 372 isp | 362 isp | | | | | | | | | | | | | | | | | | | | | 189 | 189 | 280 | 189 | 189 | 500 | 189 | | | | | | | | | | | | | | | | | | | | | 4 | 4 | 7 | 5 | 5 | ? | 15 | | | | | | | | | | | | | | | | | | | | | 600 seconds | 720 seconds | 1200 seconds | 680 seconds | 660 seconds | ? seconds | 680 seconds | | | | | | | | | | | | | | | | | | | | | 2.27 m | 2.27 m | 2.72 m | 2.27 m | 2.27 m | | 2.27 m | | | | | | | | | | | | | | | | | | | | | 1.17 m | 1.17 m | 1.4 m | 1.17 m | 1.17 m | | 1.17 m | | | | | | | | | | | | | | | | | | | | | 300 kg | 310 kg | 340 kg | 310 kg | 300 kg | | 230 kg | | | | | | | | | | | | | | | | | | | | | N-1 and Blok D | Blok DM | Blok DM-SL since 2003 and Blok DM-SLB | Blok DM-2M | Blok DM-SL | 11S861-03 | Buran | | | | | | | | | | | | | | | | | | | | | 1967-03-10 | 1974-03-26 | 2003-06-10 | 1994-10-13 | 1999-03-28 | ? | 1988-11-15 | | | | | | | | | | | | | | | | | | | | | Retired | Retired | In Production | Retired | Retired | In Production | Retired | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | ::

References

References

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2. "17D12". Encyclopedia Astronautica.
3. "Block DM-2M 11S861-01". Encyclopedia Astronautica.
4. "RD-58". Encyclopedia Astronautica.
5. "RD-58M". Encyclopedia Astronautica.
6. "RD-58MF". Encyclopedia Astronautica.
7. "RD-58S". Encyclopedia Astronautica.
8. "RD-58Z". Encyclopedia Astronautica.
9. "Engines". [[S.P. Korolev Rocket and Space Corporation Energia.
10. "Двигательная установка. 11Д58". Ecoruspace.
11. "Двигательная установка. 11Д58С". Ecoruspace.
12. "Двигательная установка. 11Д58М". Ecoruspace.
13. "Двигательная установка. 11Д58МФ". Ecoruspace.
14. (2007-10-04). "Energiya-Buran: The Soviet Space Shuttle". Springer.
15. (1998-10-12). "Энергия, Ракетно-Космическая Корпорация имени С.П.Королева, открытое акционерное общество". K204.
16. (2012). "Astronautics: Summary and Prospects". Springer Science & Business Media.
17. "Research and development". JSC Krasnoyarsk Machine-Building Plant.
18. "2014-02-28 Our Krasnoyarsk Krai "Krasmash. Future projects"". JSC Krasnoyarsk Machine-Building Plant.
19. (2014-11-10). "Владимир КолмыКоВ: "Перед Красмашем стоят серьезные задачи"". Журнал "Синева" [Magazine "Sineva"].
20. (2014-10-01). "Land Launch User's Guide (Revision B)". Space International Services.
21. (2006). "Внедрениесоплового насадка радиационного охлаждения из углерод-углеродного композиционного материала на камеру маршевого двигателя 11Д58М разгонного Блока ДМ-SL". [[S.P. Korolev Rocket and Space Corporation Energia.
22. "Block D upper stage". russianspaceweb.com.
23. "Zenit-3SL".
24. (2008). "Разработка углерод-углеродного соплового насадка для жидкостных ракетных двигателей". Thermophysics and Aeromechanics.

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