title: RD-58
text: # RD-58
  
  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. The engine was initially created to power the Block D stage of the Soviet Union's abortive N-1 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 N-1'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. 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 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. 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 (rocket) 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 (rocket) 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.
  
  RD-58 Family of Engines :
  
  | 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 | Oxidizer Rich Stage Combustion upper stage liquid rocket engine | Oxidizer Rich Stage Combustion upper stage liquid rocket engine | Oxidizer Rich Stage Combustion upper stage liquid rocket engine | Oxidizer Rich Stage Combustion upper stage liquid rocket engine | 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 | | | | | | | |
  