RD-215
| Country of origin | USSR |
|---|---|
| Date | 1958-1960 |
| Designer | OKB-456, V.Glushko |
| Associated L/V | R-14, Kosmos-3 and Kosmos-3M |
| Status | Retired |
| Liquid-fuel engine | |
| Propellant | AK-27I / UMDH |
| Mixture ratio | 2.5 |
| Configuration | |
| Chamber | 2 |
| Nozzle ratio | 18.8 |
| Performance | |
| Thrust (vac.) | 887 kN (199,000 lbf) |
| Thrust (SL) | 740 kN (170,000 lbf) |
| Chamber pressure | 7.355 MPa (1,066.8 psi) |
| Isp (vac.) | 289 s (2.83 km/s) |
| Isp (SL) | 246 s (2.41 km/s) |
| Dimensions | |
| Length | 2,205 mm (86.8 in) |
| Diameter | 2,260 mm (89 in) |
| Dry weight | 575 kg (1,268 lb) |
| Used in | |
| R-14, Kosmos-3 and Kosmos-3M first stage | |
| References | |
| References | [1][2][3][4][5][6] |
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 UMDH. It was used in a module of two engines (four nozzles) known as the RD-216 (GRAU Index 8D514).[2] 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.[1]
Versions
This engine many versions:[1]
- RD-215: GRAU Index 8D513. Original design for the R-14 (8K65). Used also on the Kosmos-1 and Kosmos-3[2][1]
- RD-215U: GRAU Index 8D513U. Improved engine for the R-14U (8K65U).[1]
- RD-215M: GRAU Index 8D513M. Improved version used on the Kosmos-3M.[1]
Modules
These engines were bundled into modules of pairs of engines. The serial production modules were:[1][3]
- RD-216: GRAU Index 8D514. Bundle of two RD-215, used on the R-14 (8K65), Kosmos-1 and Kosmos-3 first stage.[2][1]
- RD-216U: GRAU Index 8D514U. Bundle of two RD-215U, used on the R-14U (8K65U) first stage.[1]
- RD-216M: GRAU Index 8D514M. Bundle of two RD-215M, used on the Kosmos-3M first stage.[1]
| 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) / UMDH[2] | ||
| 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
References
- 1 2 3 4 5 6 7 8 9 10 11 "NPO Energomash list of engines". NPO Energomash. Retrieved 2015-06-26.
- 1 2 3 4 5 "RD-216". Encyclopedia Astronautica. Retrieved 2015-06-26.
- 1 2 "R-14". Encyclopedia Astronautica. Retrieved 2015-06-26.
- ↑ Zak, Anatoly. "Cosmos-1, 3, 3M and 3MU". RussianSpaceWeb.com. Retrieved 2016-07-05.
- ↑ Krebs, Gunter Dirk (2016-04-22). "Kosmos-1/-3/-3M". Gunter's Space Page. Retrieved 2016-07-05.
External links
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