RD-253 engine
Credit: Khrunichev
Glushko N2O4/UDMH rocket engine. 1635 kN. Isp=316s. Six gimballed single chamber RD-253s provide the first stage power for the UR-500 Proton launch vehicle. First flown in 1965.
Development went rather quickly but there were problems transitioning to production. After development is completed in Russia production moves to another plant. There was a mistake by a worker at the plant on the first engine batch and the mistake was not spotted by quality control. The first launch vehicle to use the engine shut down and the vehicle crashed. A special commission examined telemetry and several regiments of soldiers were used to collect failed vehicle parts. Luckily it was in a desert of Baikonur and not the woods and swamps surrounding Plesetsk! The RD-253 uses nitrogen tetroxide afterburning through the gas generator. A bit of fuel is added so it burns giving a hot gas. This spins up the turbine and there is no venting. It goes into the primary chamber where it is mixed with fuel. Fuel is used in the nozzle cooling system. An increase from 80 to 150 atmosphere chamber pressure was achieved to produce 150,000 kgf thrust in the first versions of this compact design. This is 167,000 kgf thrust today. There is a one-plane gimbal for the 6 engines with bellows to connect lines to tanks. This has been the basic design since 1965. First Flown: 16 July 1965. Engine Cycle: closed. Propellant Flow Rate: about 528 kg/s. Feed Method: 18.7 MW turbopump driven by pre-burner gas. Profile : 40% full thrust in 0.1 sec, held at 40% for 2 sec, then to 100% in 0.1 sec. Developed 1961-1965.
Application: Proton K-1, UR700-3.
Characteristics
Thrust (sl): 1,474.000 kN (331,368 lbf). Thrust (sl): 150,308 kgf. Engine: 1,280 kg (2,820 lb). Chamber Pressure: 152.00 bar. Area Ratio: 26. Thrust to Weight Ratio: 130.25. Oxidizer to Fuel Ratio: 2.67.
AKA: 11D48.
Unfuelled mass: 1,280 kg (2,820 lb).
Height: 2.72 m (8.92 ft).
Diameter: 1.50 m (4.90 ft).
Thrust: 1,635.00 kN (367,562 lbf).
Specific impulse: 316 s.
Specific impulse sea level: 285 s.
Burn time: 130 s.
Number: 1836 .
More... - Chronology...
Associated Countries
See also
Associated Launch Vehicles
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UR-500 Russian orbital launch vehicle. The original UR-500 two stage configuration was designed as a monster ICBM. It was flown four times from 1965, but never deployed as an operational missile. The design was succeeded by three and four stage versions for launching of large payloads into space. More...
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Proton-K/D Russian orbital launch vehicle. This four stage version of the Proton was originally designed to send manned circumlunar spacecraft into translunar trajectory. Guidance to the Block D stage must be supplied by spacecraft. The design was proposed on 8 September 1965 by Korolev as an alternate to Chelomei's LK-1 circumlunar mission. It combined the Proton 8K82K booster for the LK-1 with the N1 lunar Block D stage to boost a stripped-down Soyuz 7K-L1 spacecraft around the moon. The Korolev design was selected, and first flight came on 10 March 1967. The crash lunar program led to a poor launch record. Following a protracted ten year test period, the booster finally reached a level of launch reliability comparable to that of other world launch vehicles. More...
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Proton-K Russian orbital launch vehicle. Development of a three-stage version of the UR-500 was authorised in the decree of 3 August 1964. Decrees of 12 October and 11 November 1964 authorised development of the Almaz manned military space station and the manned circumlunar spacecraft LK-1 as payloads for the UR-500K. Remarkably, due to continuing failures, the 8K82K did not satisfactorily complete its state trials until its 61st launch (Salyut 6 / serial number 29501 / 29 September 1977). Thereafter it reached a level of launch reliability comparable to that of other world launch vehicles. More...
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Proton-K/DM Russian orbital launch vehicle. The original four stage Proton / Block D configuration was used until 1976, at which time it was replaced by a modernised version equipped with N2O4/UDMH verniers for precise placement of payloads in geosynchronous orbit and its own self-contained guidance unit. This was accepted into military service in 1978 with the first Raduga launch. The stage was first developed for launch of gesynchronous military communications and early warning satellites (Raduga, Ekran, Gorizont, Potok, SPRN). Its later versions continue in use for launch of MEO and geosynchronous comsats, and was Russia's most successful commercial launcher. More...
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Proton-K/D-1 Russian orbital launch vehicle. This derivative of the original four stage Block D / 11S824 version of the Proton was used from 1978 to launch Lavochkin OKB planetary probes (Mars, Venera) and high earth orbit astronomical observatories (Astron, Granat). Guidance to the Block D-1 stage must be supplied by spacecraft. Equipped with N2O4/UDMH verniers for precise placement of payloads in high orbits or planetary trajectories. More...
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Proton-K/DM-2 Russian orbital launch vehicle. This improved four stage version uses the Block DM-2 / 11S861 fourth stage, which has its own guidance unit. This reduces payload but does not require the spacecraft's guidance system to provide steering commands to booster. Replaced the original Block DM / 11S86 version from 1982 to 1995. Used for launch of Glonass navigation satellites into medium earth orbit; and launch of Luch, Ekran-M, Potok, Raduga, Gorizont, Raduga-1, Elektro, and Gals communications satellites into geosynchronous orbit. Commercial version with Saab payload adapter-seperation system for Western payloads was dubbed 'Block DM1'. More...
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Proton-K/DM-2 DM1 Russian orbital launch vehicle. Version of the 11S861 with adapter for Lockheed Martin AS 4000 bus spacecraft. More...
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Proton-K/D-2 Russian orbital launch vehicle. This four stage version of the Proton was a modification of the original Block D / 11S824M for launch of late 1980's Lavochkin OKB probes on missions to Mars. Guidance to the Block D-2 stage must be supplied by spacecraft. More...
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Proton-K/DM-2M This four stage version uses the Block DM-2M / 11S861-01 upper stage, which has its own self-contained guidance unit. This reduces payload but does not require the spacecraft's guidance system to provide steering commands to booster. Used for launches of Russian geosynchronous satellites from 1994 on. More...
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Proton-K/17S40 Russian orbital launch vehicle. Version of Proton using Block DM-5 / 17S40 fourth stage. This stage has a new payload adapter for use with heavier paylods launched into sub-synchronous orbits. Used for launch of Arkon reconnaisance satellite. More...
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Proton-K/17S40 DM2 Russian orbital launch vehicle. Version of the 17S40 with payload adapter for deployment of multiple LM 700 (Iridium) spacecraft into medium earth orbit. More...
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Proton-K/DM-2M DM3 Russian orbital launch vehicle. Version of the 11S861-01 with Saab payload adapter-seperation system for insertion of Hughes HS-601 bus spacecraft into geosynchronous orbit. More...
Associated Manufacturers and Agencies
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Glushko Russian manufacturer of rocket engines and rockets. Glushko Design Bureau, Russia. More...
Associated Propellants
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N2O4/UDMH Nitrogen tetroxide became the storable liquid propellant of choice from the late 1950's. Unsymmetrical Dimethylhydrazine ((CH3)2NNH2) became the storable liquid fuel of choice by the mid-1950's. Development of UDMH in the Soviet Union began in 1949. It is used in virtually all storable liquid rocket engines except for some orbital manoeuvring engines in the United States, where MMH has been preferred due to a slightly higher density and performance. More...
Associated Stages
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Proton K-1 N2O4/UDMH propellant rocket stage. Loaded/empty mass 450,510/31,100 kg. Thrust 10,470.16 kN. Vacuum specific impulse 316 seconds. More...
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R-56 Block A N2O4/UDMH propellant rocket stage. Loaded/empty mass 1,162,000/162,000 kg. Thrust 1,608.00 kN. Vacuum specific impulse 316 seconds. More...
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UR-700-3 N2O4/UDMH propellant rocket stage. Loaded/empty mass 399,400/26,000 kg. Thrust 5,139.60 kN. Vacuum specific impulse 328 seconds. More...
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