 Mock-up of a RD-275 rocket motor at theParis Air Show in 2013 | |
| Country of origin |  Soviet Union Russia |
|---|---|
| First flight | RD-253: 1965 RD-275: 1995 RD-275М: 2007 |
| Designer | NPO Energomash,Valentin Glushko |
| Manufacturer | Proton-PM |
| Application | First stage booster |
| AssociatedLV | Proton |
| Successor | RD-254, RD-256, RD-275, RD-275М |
| Status | Operational |
| Liquid-fuel engine | |
| Propellant | N2O4 /UDMH |
| Mixture ratio | 2.67 |
| Cycle | Staged combustion |
| Configuration | |
| Chamber | 1 |
| Nozzle ratio | 26.2 |
| Performance | |
| Thrust, vacuum | RD-253: 1,630 kN (370,000 lbf) RD-275: 1,750 kN (390,000 lbf) RD-275М: 1,832 kN (412,000 lbf) |
| Thrust, sea-level | RD-253: 1,470 kN (330,000 lbf) RD-275: 1,590 kN (360,000 lbf) RD-275М: 1,671 kN (376,000 lbf) |
| Thrust-to-weight ratio | 156.2 |
| Chamberpressure | RD-253: 14.7 MPa (2,130 psi; 147 bar) RD-275: 15.7 MPa (2,280 psi; 157 bar) RD-275M: 16.5 MPa (2,390 psi; 165 bar) |
| Specific impulse, vacuum | RD-253: 316s RD-275: 316s RD-275M: 315.8s |
| Specific impulse, sea-level | RD-253: 285s RD-275: 287s RD-275M: 288s |
| Gimbal range | 7.5°, single plane |
| Dimensions | |
| Length | 3 m (9.8 ft) |
| Diameter | 1.5 m (4 ft 11 in) |
| Dry mass | RD-253: 1,080 kg (2,380 lb) RD-275: 1,070 kg (2,360 lb) RD-275M: 1,070 kg (2,360 lb) |
| References | |
| References | [1][2][3][4][5][6][7] |
TheRD-253 (Russian:Ракетный Двигатель-253,romanized: Raketnyy Dvigatel-253,lit. 'Rocket Engine 253') and its later variants, theRD-275 andRD-275M, areliquid-propellant rocketengines developed in theSoviet Union byEnergomash. The engines are used on the first stage of theProton launch vehicle and use an oxidizer-richstaged combustion cycle to power the turbopumps. The engine burns ahypergolic mixture ofunsymmetrical dimethylhydrazine (UDMH) fuel withdinitrogen tetroxide (N2O4) oxidizer, which are highly toxic, but storable at room temperature.
Development of the RD-253 started in 1961. Preliminary investigations and development of the engine and its further production was performed under the guidance ofValentin Glushko and finished in 1963. The RD-253 uses anoxidiser-rich staged combustion cycle. It was used for the first time in July 1965, when six engines powered the first stage of theProton rocket. Development and production of RD-253 was a qualitative leap forward for rocketry of that time by achieving high levels ofthrust,specific impulse and pressure in thecombustion chamber. This engine is one of the most reliable engines in theUSSR and modernRussia.
As the first stage of theProton-K rocket used six RD-253 engines, the system played a pivotal role in Russianspace missions when this rocket was chosen as a carrier, including the following programs:"Luna", "Venera","Mars probe", crewedorbital stations"Salyut", "Mir", and it launched several principal modules forISS. It was widely used for the launches of heavy satellites.[1][5] The last RD-253 rocket engine was used on a Proton-K rocket and launched on March 30, 2012.[6]
Since the original development of the engine, several modifications were designed that were not flown. One of them was the RD-256 engine, for which development stopped on experimental models. It was not used in flights and was designed for a cancelled vehicle.[8] The RD-254 variant was supplied with an extended nozzle for use in vacuum.
All rights to sell and employ the RD-253 forProton rocket are held byEnergomash which produces it inPerm,Russia.
The modificationRD-275 (14D14) appeared as the result of development in 1987–1993, with the purpose to achieve a more powerful version of the engine. Its 7.7% higher thrust was reached by raising pressure in thecombustion chamber and enabled an increase ofpayload mass togeostationary orbit (GEO) up to more than 6,000 kg (13,000 lb). The successful maiden flight of aProton rocket with the new engine was completed in 1995.
Energomash started the development of next more powerful version of engine in 2001. It has 5.2% higher thrust and has the designation 14D14M (RD-275M). It was designed to allow the rocket to deliver 150 kg (330 lb) more payload toGEO.[1]
In the period from 2002 to 2003 years some experimental work was completed with this version of the engine. It included four test firings of three experimental RD-275M with a total time of 735s. In the middle of 2005, this engine went into production by government commission. The first launch of aProton-M with 14D14M engines was launched on July 7, 2007.[1]
The final version RD-275M is sometimes designated as RD-276, but through 2009 the name RD-275M (14D14M) was more common.[1][4] Some sources[which?] points out the cost of production per engine as much as 1.5 millionUSD and sometimes calls some lower figures around 1 millionUSD per unit.[citation needed]
During the years there have been many versions of this engine:
| Engine | RD-220 | RD-221 | RD-222 (11D41) | RD-223 (11D42) | RD-253 (11D413) | RD-253F (11D413F) | RD-254 (11D44) | RD-275 (14D14) | RD-275M (RD-276, 14D14M)[4] |
|---|---|---|---|---|---|---|---|---|---|
| Development | 1960 | 1960-1961 | 1962-1966 | 1966-1967 | 1961-1963 | 1987-1993 | 2001-2005 | ||
| Combustion Chamber Pressure | 14.7 MPa (2,130 psi) | 16.9 MPa (2,450 psi) | 14.7 MPa (2,130 psi) | 15.7 MPa (2,280 psi) | 16.5 MPa (2,390 psi) | ||||
| Thrust (Vacuum) | 1,074 kN (241,000 lbf) | 1,120 kN (250,000 lbf) | 1,634 kN (367,000 lbf) | 1,700 kN (380,000 lbf) | 1,635 kN (368,000 lbf) | 1,870 kN (420,000 lbf) | 1,720 kN (390,000 lbf) | 1,750 kN (390,000 lbf) | 1,832 kN (412,000 lbf) |
| Thrust (Sea Level) | 947 kN (213,000 lbf) | N/A | 1,471 kN (331,000 lbf) | N/A | 1,474 kN (331,000 lbf) | 1,720 kN (390,000 lbf) | N/A | 1,590 kN (360,000 lbf) | 1,671 kN (376,000 lbf) |
| Specific Impulse (Vacuum) | 306 s (3.00 km/s) | 318 s (3.12 km/s) | 302 s (2.96 km/s) | 314 s (3.08 km/s) | 316 s (3.10 km/s) | 317 s (3.11 km/s) | 328 s (3.22 km/s) | 316 s (3.10 km/s) | 315.8 s (3.097 km/s) |
| Specific Impulse (Sea Level) | 270 s (2.6 km/s) | N/A | 272 s (2.67 km/s) | N/A | 285 s (2.79 km/s) | 290 s (2.8 km/s) | N/A | 287 s (2.81 km/s) | 288 s (2.82 km/s) |
| Height | 2,600 mm (100 in) | 4,200 mm (170 in) | 3,470 mm (137 in) | 5,050 mm (199 in) | 3,000 mm (120 in) | 2,700 mm (110 in) | 4,000 mm (160 in) | 3,050 mm (120 in) | 3,050 mm (120 in) |
| Diameter | 1,300 mm (51 in) | 2,400 mm (94 in) | 1,460 mm (57 in) | 2,530 mm (100 in) | 1,500 mm (59 in) | 1,490 mm (59 in) | 2,600 mm (100 in) | 1,500 mm (59 in) | 1,500 mm (59 in) |
| Intended Use | N-1 first stage | N-1 second stage | N-1 first stage | N-1 second stage | Proton (8K62) first stage | R-36M (15А14) first stage | UR-700 third stage,Proton andN-1 second stages | Proton-M first stage | Proton-M first stage |
| Status | Project (Abandoned) | Retired | Project (Abandoned) | Retired | In Production | ||||
| Liquid fuel |
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