 | |
| Country of origin | USSR |
|---|---|
| First flight | 1967 |
| Designer | OKB-1,V. M. Melnikov |
| Manufacturer | Voronezh Mechanical Plant |
| Application | Upper Stage |
| AssociatedLV | N1,Proton-K,Proton-M,Zenit |
| Predecessor | S1.5400 |
| Status | In Production |
| Liquid-fuel engine | |
| Propellant | LOX /RG-1 |
| Cycle | Oxidizer-rich staged combustion |
| Configuration | |
| Chamber | 1 |
| Performance | |
| Thrust, vacuum | 79.46 kilonewtons (17,860 lbf) |
| Specific impulse, vacuum | 353 s |
| Burn time | up to 600 s |
| Dimensions | |
| Dry mass | 300 kilograms (660 lb) |
| Used in | |
| Block D | |
| References | |
| References | [1][2][3][4] |
TheRD-58 (Russian:Ракетный Двигатель-58,romanized: Raketnyy Dvigatel-58,lit. 'Rocket Engine 58',GRAU index:11D58) is arocket engine, developed in the 1960s byOKB-1, nowRKK Energia. The project was managed byMikhail Melnikov, and it was based on the previousS1.5400 engine, which was the firststaged combustion engine in the world.[1] The engine was initially created to power theBlok D stage of theSoviet Union's abortiveN1 rocket.[5] Derivatives of this stage are now used as upper stages on someProton andZenit 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 usesliquid oxygen as theoxidizer andRG-1 asfuel in anoxidizer-rich staged combustion cycle. It features a singlegimbaled chamber, radialcentrifugal pumps with auxiliary booster pumps, and an oxygen-rich preburner.[7] Recent modifications include a lightweight carbon-compositenozzle extender developed by NPO Iskra.[8][9][10]
TheBuran spacecraft used two of an evolution of theRD-58M, called17D12, as its main orbital correction engines. Instead ofRG-1, it burnedSyntin, and could be ignited 15 times.[11][12] It is assumed that it was the base for theRD-58S, which had practically the same specifications and powered theBlok DM-2M.[13] But the manufacturer states that the engine is compatible with both propellants.[1]
The current version of the engine is theRD-58M (manufacturer designation 11D58M), which has slightly reduced thrust, but increased isp. An even newer version is under development and is known as theRD-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 theBlok DM-03.[14] This new version of the engine will be built in theKrasnoyarsk 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]
This engine has had many versions through the years:
| 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 combustionupper stageliquidrocket 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 andBlok D | Blok DM | Blok DM-SL since 2003 andBlok 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] | ||||||
| Liquid fuel |
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| Solid fuel |
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Spacecraft engines and motors | ||
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| Liquid fuel engines |  | |
| Solid propellant motors | ||
| Related articles | ||