RD-58

Last updated
RD-58M
17D12.jpg
Country of origin USSR
First flight1967
Designer OKB-1, V. M. Melnikov
Manufacturer Voronezh Mechanical Plant
ApplicationUpper Stage
Associated LV N1, Proton-K, Proton-M, Zenit
Predecessor S1.5400
StatusIn Production
Liquid-fuel engine
Propellant LOX / RG-1
Cycle Oxidizer Rich Staged Combustion
Configuration
Chamber1
Performance
Thrust, vacuum79.46 kilonewtons (17,860 lbf)
Specific impulse, vacuum353 s
Burn timeup to 600 s
Dimensions
Dry mass300 kilograms (660 lb)
Used in
Block D
References
References [1] [2] [3] [4]

The RD-58 (manufacturer designation 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 which was the first staged combustion engine in the world. [1] The engine was initially created to power the Block D stage of the Soviet Union's abortive N1 rocket. [5] Derivatives of this stage are now used as upper stages on some Proton and Zenit rockets. [6] 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 LOX 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. [7] Recent modifications include a lightweight carbon-composite nozzle extender developed by NPO Iskra. [8] [9] [10]

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. [11] [12] It is assumed that it was the base for the RD-58S, which had practically the same specifications and powered the Blok DM-2M. [13] But the manufacturer states that the engine is compatible with both propellants. [1]

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 kilonewtons (11,020 lbf) 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. [14] This new version of the engine will be built in the Krasnoyarsk Machine-Building Plant. [15] [16] 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. [17]

Versions

This engine has had many versions through the years:

RD-58 Family of Engines
NameRD-58RD-58MRD-58M
(Carbon Composite Nozzle)		RD-58SRD-58ZRD-58MF17D12
Index11D5811D58M11D58S11D58Z11D58MF
Development years1964-19681970-19742000-20041986-19951981-19902002-20091981-1987
Engine Type Oxidizer Rich Stage Combustion upper stage liquid rocket engine Orbital correction liquid rocket engine
Propellant RG-1/LOX RG-1/LOX RG-1/LOX Syntin/LOX RG-1/LOX RG-1/LOX Syntin/LOX
O/F2.482.482.82 ?2.62.82 ?
Chamber Pressure7.8 MPa (1,130 psi)7.75 MPa (1,124 psi)7.9 MPa (1,150 psi)7.94 MPa (1,152 psi)7.8 MPa (1,130 psi)7.9 MPa (1,150 psi)7.94 MPa (1,152 psi)
Thrust (Vac)83.4 kN (18,700 lbf)83.4 kN (18,700 lbf)85 kN (19,000 lbf)86.3 kN (19,400 lbf)71 kN (16,000 lbf)49.03 kN (11,020 lbf)86.24 kN (19,390 lbf)
Isp (Vac)349 s (3.42 km/s)356 s (3.49 km/s)361 s (3.54 km/s)361 s (3.54 km/s)361 s (3.54 km/s)372 s (3.65 km/s)362 s (3.55 km/s)
Nozzle Expansion189189280189189500189
Ignitions44755 ?15
Burntime600 seconds720 seconds1200 seconds680 seconds660 seconds ? seconds680 seconds
Length2.27 m (89 in)2.27 m (89 in)2.72 m (107 in)2.27 m (89 in)2.27 m (89 in)2.27 m (89 in)
Diameter1.17 m (46 in)1.17 m (46 in)1.4 m (55 in)1.17 m (46 in)1.17 m (46 in)1.17 m (46 in)
Weight300 kg (660 lb)310 kg (680 lb)340 kg (750 lb)310 kg (680 lb)300 kg (660 lb)230 kg (510 lb)
Used on 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
First Launch1967-03-101974-03-262003-06-101994-10-131999-03-28 ?1988-11-15
StatusRetiredRetiredIn ProductionRetiredRetiredIn ProductionRetired
References [2] [5] [6] [7] [8] [9] [11] [12] [13] [14] [18] [19] [20] [21] [22] [23] [25]

Related Research Articles

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<span class="mw-page-title-main">RD-170</span> Soviet (now Russian) rocket engine, the most powerful in the world

The RD-170 is the world's most powerful and heaviest liquid-fuel rocket engine. It was designed and produced in the Soviet Union by NPO Energomash for use with the Energia launch vehicle. The engine burns kerosene fuel and LOX oxidizer in four combustion chambers, all supplied by one single-shaft, single-turbine turbopump rated at 170 MW (230,000 hp) in a staged combustion cycle.

<span class="mw-page-title-main">Blok D</span> Rocket stage used on Soviet and later Russian expendable launch systems

Blok D is an upper stage used on Soviet and later Russian expendable launch systems, including the N1, Proton-K and Zenit.

<span class="mw-page-title-main">RD-107</span> Russian rocket engine

The RD-107 and its sibling, the RD-108, are a type of rocket engine used on the R-7 rocket family. RD-107 engines are used in each booster and the RD-108 is used in the central core. The engines have four main combustion chambers and either two (RD-107) or four (RD-108) vernier chambers.

<span class="mw-page-title-main">RD-253</span> Soviet engine design used on the first stage of Proton rockets

The RD-253 (Russian: Ракетный Двигатель-253 (РД-253), romanized: Raketnyy Dvigatel-253, lit. 'Rocket Engine-253') and its later variants, the RD-275 and RD-275M, are liquid-propellant rocket engines developed in the Soviet Union by Energomash. The engines are used on the first stage of the Proton launch vehicle and use an oxidizer-rich staged combustion cycle to power the turbopumps. The engine burns UDMH/N2O4, which are highly toxic but hypergolic and storable at room temperature, simplifying the engine's design.

The RD-120 is a liquid upper stage rocket engine burning RG-1 and LOX in an oxidizer rich staged combustion cycle with an O/F ratio of 2.6. It is used in the second stage of the Zenit family of launch vehicles. It has a single, fixed combustion chamber and thus on the Zenit it is paired with the RD-8 vernier engine. The engine was developed from 1976 to 1985 by NPO Energomash with V.P. Radovsky leading the development. It is manufactured by, among others, Yuzhmash in Ukraine.

The Blok DM-03, GRAU index 11S861-03, is a Russian upper stage used as an optional fourth stage on the Proton-M and Angara A5 heavy-lift rockets. Three have been launched, the first in December 2010; the first two launches failed before fourth stage ignition, the first as a result of a problem with the Blok DM's fuel load. Some versions are also known as Orion.

<span class="mw-page-title-main">S1.5400</span> First staged combustion rocket engine ever developed, for the Soviet space program

The S1.5400 was a Soviet single-nozzle liquid-propellant rocket engine burning liquid oxygen and kerosene in an oxidizer-rich staged combustion cycle, being the first rocket engine to use this cycle in the world. It was designed by V. M. Melnikov, an alumnus of Isaev, within Korolev's Bureau, for the Molniya fourth stage, the Block-L. It was also the first Soviet engine designed for start and restart in vacuum and had the highest Isp at the time of its deployment.

<span class="mw-page-title-main">RD-0210</span>

The RD-0210 (GRAU Index: 8D411K) is also known as the RD-465. It and its twin, the RD-0211, are rocket engines burning N2O4 and UDMH in an oxidizer rich staged combustion cycle. They have single nozzle, possess TVC and are the latest evolution in the RD-0203/4 lineage. They are the engines used on the Proton second stage. The RD-0213 is a fixed nozzle variation that is used on the RD-0212 module of the Proton third stage.

The RD-0216 and RD-0217 are liquid rocket engines, burning N2O4 and UDMH in the oxidizer rich staged combustion cycle. The only difference between the RD-0216 and the RD-0217 is that the latter doesn't have a heat exchanger to heat the pressuring gasses for the tanks. Three RD-0216 and one RD-0217 were used on the first stage of the UR-100 ICBM. The engines were manufactured until 1974 and stayed in operational use until 1991. More than 1100 engines were produced.

The RD-0237 (GRAU Index 15D114) is a pressure-fed liquid rocket vernier engine, burning N2O4 and UDMH. It is used on the UR-100UTTKh MIRV vehicle to supply thrust vector control by gimbaling of its nozzle. While the engine is out of production, the ICBM and Strela remain operational as of 2015.

The RD-263 (GRAU Index 15D117) is a liquid rocket engine, burning N2O4 and UDMH in the oxidizer rich staged combustion cycle. Four RD-263 engines form a propulsion module RD-264 (GRAU Index 15D119). For the R-36M KB Yuzhnoye only ordered the first stage propulsion to Energomash, instead of both stages, arguing that they were overworked with the RD-270 development. By April 1970 Yuzhnoye was getting the engine documentation. By the end of 1972 Energomash started to test fire the engines in its own test stand. And by September 1973 the engine was certified for flight. While the engine is out of production, the ICBM as well as the Dnepr remain operational as of 2015.

<span class="mw-page-title-main">RD-119</span>

The RD-119 was a liquid rocket engine, burning liquid oxygen and UDMH in the gas-generator cycle. It has a huge expansion ratio on the nozzle and uses a unique propellant combination to achieve an extremely high isp of 352 s for a semi-cryogenic gas-generator engine. It also has a unique steering mechanism. The engine main nozzle is fixed, and the output of the gas generator is fed into four nozzles on the side of the engine. Instead of using gimbaled verniers to supply vector control, the combustion gases are distributed by an electrically driven system that can control the thrust among the nozzles.

<span class="mw-page-title-main">RD-214</span> Rocket engine

The RD-214 (GRAU Index 8D59) was a liquid rocket engine, burning AK-27I (a mixture of 73% nitric acid and 27% N2O4 + iodine passivant and TM-185 (a kerosene and gasoline mix) in the gas generator cycle. As was the case with many V-2 influenced engines, the single turbine was driven by steam generated by catalytic decomposition of hydrogen peroxide. It also had four combustion chambers and vector control was achieved by refractory vanes protruding into the nozzle's exhaust.

The KTDU-35 was a Soviet spacecraft propulsion system composed of two liquid rocket engines, the primary, S5.60 (SKD) and the secondary S5.35 (DKD), fed from the same propellant tanks. Both engines burn UDMH and AK27I in the gas generator cycle. It was designed by OKB-2, the famous Isaev Design Bureau, for the original Soyuz programme.

The 11D428A-16 (manufacturer's name RDMT-135M) is a liquid pressure-fed rocket engine burning N2O4/UDMH with an 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. The 11D428A-16 generates 129.16 N (29.04 lbf) of thrust with a chamber pressure of 0.88 MPa (128 psi) and achieves a specific impulse of 291 s (2.85 km/s). It is rated for 500,000 starts with a certified ignition time of 0.03 seconds to 2000 seconds. Each unit weights 1.5 kg (3.3 lb).

<span class="mw-page-title-main">RD-250</span> Rocket engine

The RD-250 (GRAU Index 8D518) is the base version of a dual-nozzle family of liquid rocket engines, burning N2O4 and UDMH in the gas-generator open cycle. The RD-250 was developed by OKB-456 for Yangel's PA Yuzhmash ICBM, the R-36 (8K67). Its variations were also used on the Tsyklon-2 and Tsyklon-3 launch vehicles. It was supposed to be used on the Tsyklon-4, but since the cancellation of the project it should be considered as out of production.

<span class="mw-page-title-main">RD-215</span> Rocket engine

The RD-215 (GRAU Index 8D513) was a dual nozzle liquid rocket engine, burning AK-27 (a mixture of 73% nitric acid and 27% N2O4 + iodine passivant) and UDMH. It was used in a module of two engines (four nozzles) known as the RD-216 (GRAU Index 8D514). The RD-215 was developed by OKB-456 for Yangel's Yuzhmash R-14 (8K65) ballistic missile. Its variations were also used on the Kosmos-1, Kosmos-3 and Kosmos-3M launch vehicles.

The RD-861 is a Soviet liquid propellant rocket engine burning UDMH and nitrogen tetroxide in a gas generator combustion cycle. It has a main combustion chamber, with four vernier nozzles fed by the gas generator output. It can be reignited a single time.

The RD-864 is a Soviet liquid propellant rocket engine burning UDMH and nitrogen tetroxide in a gas generator combustion cycle. It has a four combustion chambers that provide thrust vector control by gimbaling each nozzle in a single axis ±55°. It is used on the third stage of the R-36M UTTKh and Dnepr. For the R-36M2, an improved version, the RD-869 was developed. The MEA is an evolution of the RD-869 used on the Vega C.

References

  1. 1 2 3 "Engines". RSC Energiya Official Page. RSC Energiya . Retrieved 2015-08-01.
  2. 1 2 "DESCRIPTION OF ZENIT-2SLB, ZENIT-3SLB, ZENIT-3SLBF INTEGRATED LAUNCH VEHICLES". Land Launch User's Guide (Revision B) (PDF). Space International Services. 2014-10-01. p. 29. Archived from the original (PDF) on 2016-06-25. Retrieved 2015-06-03.
  3. ↑ Kiselev, Anatoli I.; Medvedev, Alexander A.; Menshikov, Valery A. (2012). "Section 2.2.2 Carrier rocket booster units". Astronautics: Summary and Prospects. Springer Science & Business Media. pp. 304–305. ISBN   978-3709106488.
  4. ↑ Zak, Anatoly. "Block D upper stage". russianspaceweb.com. Retrieved 2015-06-03.
  5. 1 2 3 "RD-58". Encyclopedia Astronautica. Archived from the original on 2016-08-03. Retrieved 2015-07-31.
  6. 1 2 "Zenit-3SL". Spaceflight 101. Retrieved July 14, 2014.
  7. 1 2 3 "Двигательная установка. 11Д58М" [The propulsion system. 11D58M] (in Russian). Ecoruspace. Retrieved 2015-07-31.
  8. 1 2 3 Sokolovskiy, M.I.; Petukhov, S.N.; Semenov, Yu.P.; Sokolov, B.A. (2008). "Разработка углерод-углеродного соплового насадка для жидкостных ракетных двигателей" [The development of carbon-carbon nozzle extension for liquid rocket engines](PDF). Thermophysics and Aeromechanics (in Russian). 15 (4): 721–727. Retrieved 2015-08-02.
  9. 1 2 3 4 Mezhevov, A.V.; Skoromnov, V.I.; Kozlov, A.V.; Tupitsin, N.N.; Khaskekov, V.G. (2006). "Внедрениесоплового насадка радиационного охлаждения из углерод-углеродного композиционного материала на камеру маршевого двигателя 11Д58М разгонного Блока ДМ-SL" [Installation of a Radiation-Cooled Nozzle of Carbon-Carbon Composite Material to the Combustion Chamber of Main Engine 11D58M of Block DM-SL](PDF). Вестник СГАУ [Bulletin SSAU] (in Russian) (2-2 (10) 2006). RSC Energia . Retrieved 2015-08-01.
  10. 1 2 "Раздвижные сопла и сопловые насадки для РДТТ и ЖРД" [Extendable nozzle and nozzle extensions for SRM and LRE]. www.npoiskra.ru (in Russian). NPO Iskra. Archived from the original on 4 March 2016.
  11. 1 2 3 "17D12". Encyclopedia Astronautica. Archived from the original on 2016-08-03. Retrieved 2015-07-31.
  12. 1 2 3 Hendrickx, Bart; Vis, Bert (2007-10-04). Energiya-Buran: The Soviet Space Shuttle (UK 2007 ed.). Springer. pp. 127–131. ISBN   978-0-387-69848-9 . Retrieved 2015-08-01.
  13. 1 2 3 "Block DM-2M 11S861-01". Encyclopedia Astronautica. Archived from the original on 2006-06-14. Retrieved 2015-07-31.
  14. 1 2 "Двигательная установка. 11Д58МФ" [The propulsion system. 11D58MF] (in Russian). Ecoruspace. Retrieved 2015-07-31.
  15. ↑ "Research and development". www.krasm.com (in Russian). JSC Krasnoyarsk Machine-Building Plant. Retrieved 2015-06-10.
  16. ↑ "2014-02-28 Our Krasnoyarsk Krai "Krasmash. Future projects"". www.krasm.com (in Russian). JSC Krasnoyarsk Machine-Building Plant. Retrieved 2015-06-10.
  17. ↑ Galina Yakovleva (2014-11-10). "Владимир КолмыКоВ: "Перед Красмашем стоят серьезные задачи"" [Vladimir Kolmykov: "Serious challenges ahead for Krasmash"](PDF). Журнал "Синева" [Magazine "Sineva"] (in Russian). 2014 (Sineva № 7-8): 2. Retrieved 2015-08-03.
  18. 1 2 "Двигательная установка. 11Д58" [The propulsion system. 11D58] (in Russian). Ecoruspace. Retrieved 2015-07-31.
  19. 1 2 "RD-58M". Encyclopedia Astronautica. Archived from the original on March 19, 2002. Retrieved 2015-07-31.
  20. 1 2 "RD-58MF". Encyclopedia Astronautica. Archived from the original on 2016-08-03. Retrieved 2015-07-31.
  21. 1 2 "RD-58S". Encyclopedia Astronautica. Archived from the original on 2016-08-03. Retrieved 2015-07-31.
  22. 1 2 "Двигательная установка. 11Д58С" [The propulsion system. 11D58S] (in Russian). Ecoruspace. Retrieved 2015-07-31.
  23. 1 2 "RD-58Z". Encyclopedia Astronautica. Archived from the original on 2016-08-03. Retrieved 2015-07-31.
  24. ↑ "17D11". Encyclopedia Astronautica. Archived from the original on March 19, 2002. Retrieved 2015-07-31.
  25. ↑ "Энергия, Ракетно-Космическая Корпорация имени С.П.Королева, открытое акционерное общество" [Open Joint Stock Company S.P. Korolev Rocket and Space Corporation Energia](PDF) (in Russian). K204. 1998-10-12. Retrieved 2015-08-03.
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