| RD-215 (РД-215) | |
| Country Of Origin: | USSR |
| Date: | 1958-1960 |
| Designer: | OKB-456, V.Glushko |
| Associated: | R-14, Kosmos-3 and Kosmos-3M |
| Status: | Retired |
| Type: | liquid |
| Oxidiser: | AK-27I |
| Fuel: | UDMH |
| Mixture Ratio: | 2.5 |
| Combustion Chamber: | 2 |
| Nozzle Ratio: | 18.8 |
| Thrust(Vac): | 887kN |
| Thrust(Sl): | 740kN |
| Chamber Pressure: | 7.355MPa |
| Specific Impulse Vacuum: | 289isp |
| Specific Impulse Sea Level: | 246isp |
| Length: | 2205mm |
| Diameter: | 2260mm |
| Dry Weight: | 575kg (1,268lb) |
| Used In: | R-14, Kosmos-3 and Kosmos-3M first stage |
The RD-215 (GRAU Index 8D513) was a dual nozzle liquid rocket engine, burning AK-27 (a mixture of 73% nitric acid and 27% N2O4 + iodine passivant) and UDMH. It was used in a module of two engines (four nozzles) known as the RD-216 (GRAU Index 8D514). The RD-215 was developed by OKB-456 for Yangel's Yuzhmash R-14 (8K65) ballistic missile. Its variations were also used on the Kosmos-1, Kosmos-3 and Kosmos-3M launch vehicles.
The family incorporate many versions:[1]
These engines were bundled into modules of pairs of engines. The serial production modules were:
| Engine | RD-215 | RD-215U | RD-215M | |
|---|---|---|---|---|
| GRAU | 8D514 | 8D514U | 8D514M | |
| Development | 1958-1960 | 1960-1961 | 1966-1968 | |
| Propellant | AK-27I (73% nitric acid, 27% N2O4, and iodine passivant) / UDMH | |||
| Combustion chamber pressure | 7.355MPa | |||
| Thrust, vacuum | 887kN | 887kN | 890kN | |
| Thrust, sea level | 740kN | 740kN | 742.8kN | |
| I, vacuum | 289isp | 289isp | 291.3isp | |
| I, sea level | 246isp | 246isp | 248isp | |
| Burn time | 146s | N/A | N/A | |
| Length | 2205mm | 2205mm | 2205mm | |
| Diameter | 2260mm | 2260mm | 2260mm | |
| Dry weight | 575kg (1,268lb) | 575kg (1,268lb) | 570kg (1,260lb) | |
| Use | R-14U (8K65U) | Kosmos-3M | ||