|Country of origin||USSR|
|Designer||OKB-1, V. M. Melnikov|
|Manufacturer||Voronezh Mechanical Plant|
|Associated LV||N-1, Proton-K, Proton-M, Zenit|
|Propellant||LOX / RP-1|
|Cycle||Oxidizer Rich Staged Combustion|
|Thrust (vacuum)||79.46 kilonewtons (17,860 lbf)|
|Specific impulse (vacuum)||353 sec|
|Burn time||up to 600s|
|Dry weight||300 kilograms (660 lb)|
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.
This engine has had many versions through the years:
(Carbon Composite Nozzle)
|Engine Type||Oxidizer Rich Stage Combustion upper stage liquid rocket engine||Orbital correction liquid rocket engine|
|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)|
|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|
|Status||Retired||Retired||In Production||Retired||Retired||In Production||Retired|