RD-58M
| Country of origin | USSR |
|---|---|
| First flight | 1967 |
| Designer | OKB-1, V. M. Melnikov |
| Manufacturer | Voronezh Mechanical Plant |
| Application | Upper Stage |
| Associated L/V | N-1, Proton-K, Proton-M, Zenit |
| Predecessor | S1.5400 |
| Status | In Production |
| Liquid-fuel engine | |
| Propellant | LOX / RG-1 |
| Cycle | Oxidizer Rich Stage Combustion |
| Configuration | |
| Chamber | 1 |
| Performance | |
| Thrust (vac.) | 79.46 kilonewtons (17,860 lbf) |
| Isp (vac.) | 353 sec |
| Burn time | up to 600s |
| Dimensions | |
| Dry weight | 300 kilograms (660 lb) |
| Used in | |
| Block D | |
| References | |
| References | |
The RD-58 (manufacturer designation 11D58) was 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 stage 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 stage 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.
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