RD-275
| Country of origin | USSR/Russia |
|---|---|
| First flight |
RD-253: 1965 RD-275: 1995 RD-275М: 2007 |
| Designer | Energomash, V.Glushko |
| Manufacturer | Proton-PM |
| Application | First stage booster |
| Associated L/V | 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 (vac.) |
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 (SL) |
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 | 159,2 |
| Chamber pressure |
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) |
| Isp (vac.) |
RD-253: 316s RD-275: 316s RD-275M: 315.8s |
| Isp (SL) |
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 weight |
RD-253: 1,080 kg (2,380 lb) RD-275: 1,070 kg (2,360 lb) RD-275M: 1,070 kg (2,360 lb) |
| Used in | |
| Proton first stage. | |
| References | |
| References | |
The RD-253 (Russian: Раке́тный дви́гатель 253, Rocket Engine 253) and its later variants, the RD-275 and RD-275M, are liquid-propellant rocket engines developed in the Soviet Union by Energomash. The engines are used on the first stage of the Proton launch vehicle and use an oxidizer-rich staged combustion cycle to power the turbopumps. The engine burns UDMH/N2O4, which are highly toxic but hypergolic and storable at room temperature, simplifying the design.
Development of RD-253 started in 1961. Preliminary investigations and development of the engine as well as its further production was performed under the guidance of Valentin Glushko and finished in 1963. The RD-253 uses a staged combustion cycle for oxidizer-rich generator gas. It was used for the first time in July 1965 year when six engines powered the first stage of the rocket. Development and production of RD-253 was a qualitative leap forward for rocketry of that time by achieving high levels of thrust, specific impulse and pressure in the combustion chamber. This engine is one of the most reliable engines in the USSR and modern Russia.
As every first stage of Proton-K rockets used six RD-253 engines, the system played a pivotal role in Russian space missions when this rocket was chosen as carrier, including the following programs: "Luna", "Venera", "Mars probe", manned orbital stations "Salyut", "Mir" and it supplied several principal modules for ISS. It is used widely also for heavy satellites launches. The last RD-253 rocket engine was used on Proton-K rocket and launched on March 30, 2012.
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