 Museum of Space and Missile Technology (Saint Petersburg). RD-119 rocket engine for Cosmos LV(11К63) second stage. | |
| Country of origin | USSR |
|---|---|
| Date | 1960–1963[1] |
| Designer | Energomash,V. Glushko[1] |
| AssociatedLV | Kosmos-2[1] |
| Status | Out of production |
| Liquid-fuel engine | |
| Propellant | LOX[2] /UDMH[2] |
| Mixture ratio | 1.5[2] |
| Cycle | Gas generator[2][3] |
| Configuration | |
| Chamber | 1[2] |
| Nozzle ratio | 102 |
| Performance | |
| Thrust, vacuum | 106 kilonewtons (24,000 lbf)[1] |
| Thrust, sea-level | 65.6 kilonewtons (14,700 lbf)[2] |
| Chamberpressure | 7.9 megapascals (1,150 psi)[1] |
| Specific impulse, vacuum | 352 s (3.45 km/s)[1] |
| Specific impulse, sea-level | 220 s (2.2 km/s)[2] |
| Burn time | 260 s[2] |
| Gimbal range | Fixed with four fixed steering nozzles |
| Dimensions | |
| Length | 2,170 millimetres (85 in)[1] |
| Diameter | 1,024 millimetres (40.3 in)[1] |
| Dry mass | 168.5 kilograms (371 lb)[1] |
| Used in | |
| Kosmos-2 (11K63)[1] | |
TheRD-119 (GRAU Index8D710) was aliquidrocket engine, burningliquid oxygen andUDMH in thegas-generator cycle.[3] It has a huge expansion ratio on the nozzle and uses a unique propellant combination to achieve an extremely highisp of 352 s for a semi-cryogenic gas-generator engine. It also has a unique steering mechanism. The engine main nozzle is fixed, and the output of the gas generator is fed into four nozzles on the side of the engine. Instead of usinggimbaledverniers to supplyvector control, the combustion gases are distributed by an electrically driven system that can control the thrust among the nozzles.
Between 1958 and 1960,Valentin Glushko's OKB 456 developed theRD-109 for the Block-I of the 8K73 project — aliquid-oxygen/UDMH version of theR-7. ButSergei Korolev's refusal to use such a toxic combination shelved the project.[4] WhenMikhail Yangel'sOKB-586 was tasked with developing a launch vehicle out of theR-12 ballistic missile, they had to develop an upper stage from scratch. The critical issue was the low specific impulse of the first stage, and thus a very high-efficiency upper-stage engine was needed. For this Glushko offered to adapt the RD-109, and Yangel accepted the proposal.[3] It flew some very important missions on the Kosmos-2 launch vehicle, with about 165 engines produced.[2][5]
This engine had two versions.
| Engine | RD-109 | RD-119 |
|---|---|---|
| AKA | 8D711 or GDU-10 | 8D710 |
| Development | 1957–1960[4] | 1960–1963[2] |
| Engine type | Gas generator[2][3] | |
| Propellant | LOX/UDMH[2] | |
| Combustion-chamber pressure | 7.75 MPa (1,124 psi)[1] | 7.9 MPa (1,150 psi)[1] |
| Thrust (vacuum) | 101.6 kN (22,800 lbf)[1] | 106 kN (24,000 lbf)[1] |
| Thrust (sea level) | N/A | 65.6 kN (14,700 lbf)[2] |
| Isp (vacuum) | 334 s (3.28 km/s)[1] | 352 s (3.45 km/s)[1] |
| Isp (sea level) | N/A | 220 s (2.2 km/s)[2] |
| Burn time | 330 s[4] | 260 s[2] |
| Length | 2,280 mm (90 in)[1] | 2,170 mm (85 in)[1] |
| Diameter | 1,024 mm (40.3 in)[1] | 1,024 mm (40.3 in)[1] |
| Dry mass | 210 kg (460 lb)[1] | 168.5 kg (371 lb)[1] |
| Use | 8K73 project | Kosmos-2 |
Gluschko, V. P. (1985).Kosmonavtika Entsiklopediya - Cosmonautic Encyclopedia (Russian) -Космонавтика Энциклопедия(PDF). Moscow. p. 329.Archived(PDF) from the original on 11 July 2022.{{cite book}}: CS1 maint: location missing publisher (link)
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