Contents

RD-58

1967

OKB-1, V. M. Melnikov

Voronezh Mechanical Plant

Upper Stage

N-1, Proton-K, Proton-M, Zenit

S1.5400

In Production

LOX / RP-1

Oxidizer Rich Staged Combustion

1

79.46 kilonewtons (17,860 lbf)

353 s

up to 600 s

300 kilograms (660 lb)

^[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 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-1asfuel 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[edit]

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]

RD-58M

RD-58M
(Carbon Composite Nozzle)

RD-58S

RD-58Z

RD-58MF

17D12

11D58

11D58M

11D58S

11D58Z

11D58MF

1964-1968

1970-1974

2000-2004

1986-1995

1981-1990

2002-2009

1981-1987

Oxidizer Rich Stage Combustion upper stage liquid rocket engine

Orbital correction liquid rocket engine

RG-1/LOX

RG-1/LOX

RG-1/LOX

Syntin/LOX

RG-1/LOX

RG-1/LOX

Syntin/LOX

2.48

2.48

2.82

?

2.6

2.82

?

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)

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)

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)

189

189

280

189

189

500

189

4

4

7

5

5

?

15

600 seconds

720 seconds

1200 seconds

680 seconds

660 seconds

? seconds

680 seconds

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)

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)

300 kg (660 lb)

310 kg (680 lb)

340 kg (750 lb)

310 kg (680 lb)

300 kg (660 lb)

230 kg (510 lb)

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

1967-03-10

1974-03-26

2003-06-10

1994-10-13

1999-03-28

?

1988-11-15

Retired

Retired

In Production

Retired

Retired

In Production

Retired

^{[2][5][6][7][8][9][11][12][13][14][18][19][20][21][22][23][25]}

References[edit]