RD-215
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The RD-215 (Russian: Ракетный Двигатель-215, romanized:Raketnyy Dvigatel-215, lit.'Rocket Engine 215', GRAU index: 8D513) was a dual nozzle liquid-fuel rocket engine, burning a hypergolic mixture of unsymmetrical dimethylhydrazine (UDMH) fuel with AK-27 oxidizer (a mixture of 73% nitric acid and 27% dinitrogen tetroxide [N2O4] with iodine as a passivant). 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.
Versions
The family incorporate many versions:
- RD-215 (GRAU index: 8D513): Original design for the R-14 (8K65). Used also on the Kosmos-1 and Kosmos-3
- RD-215U (GRAU index: 8D513U): Improved engine for the R-14U (8K65U).
- RD-215M (GRAU index: 8D513M): Improved version used on the Kosmos-3M.
- RD-218 (GRAU index: 8D515): Modified design for the R-16 (8K64) first stage.
- RD-219 (GRAU index: 8D713): Modified design for the R-16 (8K64) second stage.
Modules
These engines were bundled into modules of pairs of engines. The serial production modules were:
- RD-216 (GRAU index: 8D514): Bundle of two RD-215, used on the R-14 (8K65), Kosmos-1 and Kosmos-3 first stage.
- RD-216U (GRAU index: 8D514U): Bundle of two RD-215U, used on the R-14U (8K65U) first stage.
- RD-216M (GRAU index: 8D514M): Bundle of two RD-215M, used on the Kosmos-3M first stage.
- RD-218 (GRAU index: 8D712): Bundle of three RD-217, powers the R-16 (8K64) first stage.
| 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 | 7.355 MPa (1,066.8 psi) | ||
| Thrust, vacuum | 887 kN (199,000 lbf) | 887 kN (199,000 lbf) | 890 kN (200,000 lbf) |
| Thrust, sea level | 740 kN (170,000 lbf) | 740 kN (170,000 lbf) | 742.8 kN (167,000 lbf) |
| Isp, vacuum | 289 s (2.83 km/s) | 289 s (2.83 km/s) | 291.3 s (2.857 km/s) |
| Isp, sea level | 246 s (2.41 km/s) | 246 s (2.41 km/s) | 248 s (2.43 km/s) |
| Burn time | 146s | N/A | N/A |
| Length | 2,205 mm (86.8 in) | 2,205 mm (86.8 in) | 2,205 mm (86.8 in) |
| Diameter | 2,260 mm (89 in) | 2,260 mm (89 in) | 2,260 mm (89 in) |
| Dry weight | 575 kg (1,268 lb) | 575 kg (1,268 lb) | 570 kg (1,260 lb) |
| Use | R-14 (8K65), Kosmos-1 and Kosmos-3 | R-14U (8K65U) | Kosmos-3M |
See also
- R-14 - Ballistic missile for which this engine was originally developed for.
- Kosmos-3 - launch vehicle that is uses an R-14 as first stage.
- Kosmos-3M - launch vehicle that is uses an R-14 as first stage.
- Rocket engine using liquid fuel