RD-58
| Country of origin | USSR |
|---|---|
| First flight | 1967 |
| Designer | OKB-1, V. M. Melnikov |
| Manufacturer | Voronezh Mechanical Plant |
| Application | Upper Stage |
| Associated L/V | N-1, Proton-K, Proton-M, Zenit |
| Predecessor | S1.5400 |
| Status | In Production |
| Liquid-fuel engine | |
| Propellant | LOX / RG-1 |
| Cycle | Oxidizer Rich Stage Combustion |
| Configuration | |
| Chamber | 1 |
| Performance | |
| Thrust (vac.) | 79.46 kilonewtons (17,860 lbf) |
| Isp (vac.) | 353 sec |
| Burn time | up to 600s |
| Dimensions | |
| Dry weight | 300 kilograms (660 lb) |
| Used in | |
| Block D | |
| References | |
| References | [1][2][3][4] |
The RD-58 (manufacturer designation 11D58) was 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 stage combustion engine in the world.[1] The engine was initially created to power the Block D stage of the Soviet Union's abortive N-1 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 N-1's roll-control engine.
The RD-58 uses LOX as the oxidizer and RG-1 as fuel in an oxidizer rich stage 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 (GRAU Index 11D58): Original version developed for the Blok D of the N1 (rocket).[5][18]
- RD-58M (GRAU Index 11D58M): Improved version developed for the Proton (rocket) Blok D.[7][19]
- 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.[8][9][10]
- RD-58MF (GRAU Index 11D58MF): Reduced thrust and increased specific impulse version expected to fly on the Proton and Zenit (rocket) Blok DM-03. Will probably also use a carbon-carbon nozzle extension.[20]
- 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.[13][21][22]
- RD-58Z (GRAU Index 11D58Z): Version adapted to the Zenit Blok DM-SL.[9][23]
- 17D12: Orbital maneuvering engines (DOM) of the Buran propulsion system 17D11, burned Syntin/LOX.[11][12][24]
| Name | RD-58 | RD-58M | RD-58M (Carbon Composite Nozzle) |
RD-58S | RD-58Z | RD-58MF | 17D12 |
|---|---|---|---|---|---|---|---|
| Index | 11D58 | 11D58M | 11D58S | 11D58Z | 11D58MF | ||
| Development years | 1964-1968 | 1970-1974 | 2000-2004 | 1986-1995 | 1981-1990 | 2002-2009 | 1981-1987 |
| 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/F | 2.48 | 2.48 | 2.82 | ? | 2.6 | 2.82 | ? |
| Chamber Pressure | 7.8 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 Expansion | 189 | 189 | 280 | 189 | 189 | 500 | 189 |
| Ignitions | 4 | 4 | 7 | 5 | 5 | ? | 15 |
| Burntime | 600 seconds | 720 seconds | 1200 seconds | 680 seconds | 660 seconds | ? seconds | 680 seconds |
| Length | 2.27 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) | |
| Diameter | 1.17 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) | |
| Weight | 300 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 Launch | 1967-03-10 | 1974-03-26 | 2003-06-10 | 1994-10-13 | 1999-03-28 | ? | 1988-11-15 |
| Status | Retired | Retired | In Production | Retired | Retired | In Production | Retired |
| References | [2][5][6][7][8][9][11][12][13][14][18][19][20][21][22][23][25] | ||||||
References
- 1 2 3 "Engines". RSC Energiya Official Page. RSC Energiya. Retrieved 2015-08-01.
- 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. Retrieved 2015-06-03.
- ↑ 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.
- ↑ Zak, Anatoly. "Block D upper stage". russianspaceweb.com. Retrieved 2015-06-03.
- 1 2 3 "RD-58". Encyclopedia Astronautica. Retrieved 2015-07-31.
- 1 2 "Zenit-3SL". Spaceflight 101. Retrieved July 2014. Check date values in:
|access-date=(help) - 1 2 3 "Двигательная установка. 11Д58М" [The propulsion system. 11D58M] (in Russian). Ecoruspace. Retrieved 2015-07-31.
- 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 (N°4): 721–727. Retrieved 2015-08-02.
- 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). RSC Energia (2-2 (10) 2006). Retrieved 2015-08-01.
- 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. Retrieved 2015-08-02.
- 1 2 3 "17D12". Encyclopedia Astronautica. Retrieved 2015-07-31.
- 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.
- 1 2 3 "Block DM-2M 11S861-01". Encyclopedia Astronautica. Retrieved 2015-07-31.
- 1 2 "Двигательная установка. 11Д58МФ" [The propulsion system. 11D58MF] (in Russian). Ecoruspace. Retrieved 2015-07-31.
- ↑ "Research and development". www.krasm.com (in Russian). JSC Krasnoyarsk Machine-Building Plant. Retrieved 2015-06-10.
- ↑ "2014-02-28 Our Krasnoyarsk Krai "Krasmash. Future projects"". www.krasm.com (in Russian). JSC Krasnoyarsk Machine-Building Plant. Retrieved 2015-06-10.
- ↑ 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.
- 1 2 "Двигательная установка. 11Д58" [The propulsion system. 11D58] (in Russian). Ecoruspace. Retrieved 2015-07-31.
- 1 2 "RD-58M". Encyclopedia Astronautica. Retrieved 2015-07-31.
- 1 2 "RD-58MF". Encyclopedia Astronautica. Retrieved 2015-07-31.
- 1 2 "RD-58S". Encyclopedia Astronautica. Retrieved 2015-07-31.
- 1 2 "Двигательная установка. 11Д58С" [The propulsion system. 11D58S] (in Russian). Ecoruspace. Retrieved 2015-07-31.
- 1 2 "RD-58Z". Encyclopedia Astronautica. Retrieved 2015-07-31.
- ↑ "17D11". Encyclopedia Astronautica. Retrieved 2015-07-31.
- ↑ "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.
Orbital spacecraft rocket engines and motors that have flown | ||
|---|---|---|
| Liquid fuel engines |  | |
| Solid propellant motors | ||
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