Country of origin | USSR |
---|---|
First flight | 1967 |
Designer | OKB-1, V. M. Melnikov |
Manufacturer | Voronezh Mechanical Plant |
Application | Upper Stage |
Associated LV | 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] |
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 N1 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 N1'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.[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]
energiya-rd58m
was invoked but never defined (see the help page).llug-2014
was invoked but never defined (see the help page).kiselev-crbu
was invoked but never defined (see the help page).rsw-blockd
was invoked but never defined (see the help page).ea-rd58
was invoked but never defined (see the help page).sf101-zenit3sl
was invoked but never defined (see the help page).ers-11d58m
was invoked but never defined (see the help page).sokolovskiy-2008
was invoked but never defined (see the help page).mezhevov-2006
was invoked but never defined (see the help page).npoiskra-products
was invoked but never defined (see the help page).ea-17d12
was invoked but never defined (see the help page).hendrckx2007
was invoked but never defined (see the help page).ea-blo86101
was invoked but never defined (see the help page).ers-11d58mf
was invoked but never defined (see the help page).krasm-direct
was invoked but never defined (see the help page).krasm-news20140228
was invoked but never defined (see the help page).krasm-sineva201478
was invoked but never defined (see the help page).