Proton-K

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Proton-K
Proton Zvezda crop.jpg
Launch of a Proton-K with Zvezda
Function Heavy carrier rocket
Manufacturer Khrunichev
Country of origin  Soviet Union
 Russia
Size
Height 50 metres (160 ft)
Diameter 7.4 metres (24 ft)
Stages 3 or 4
Associated rockets
Family Universal Rocket
Launch history
Status Retired
Launch sites Baikonur Sites 81 & 200
Total launches 311
First flight 10 March 1967[1]
Last flight 30 March 2012
First Stage
Length 21.2 metres (70 ft)
Diameter 7.4 metres (24 ft)
Empty mass 31,100 kilograms (68,600 lb)
Gross mass 450,510 kilograms (993,200 lb)
Engines 6 RD-253-14D48
Thrust 10,470 kilonewtons (2,350,000 lbf)
Specific impulse 316 sec
Burn time 124 seconds
Fuel N2O4/UDMH
Second Stage - 8S811K
Length 14 metres (46 ft)
Diameter 4.15 metres (13.6 ft)
Empty mass 11,715 kilograms (25,827 lb)
Gross mass 167,828 kilograms (369,997 lb)
Engines 4 RD-0210
Thrust 2,399 kilonewtons (539,000 lbf)
Specific impulse 327 sec
Burn time 206 seconds
Fuel N2O4/UDMH
Third Stage
Length 6.5 metres (21 ft)
Diameter 4.15 metres (13.6 ft)
Empty mass 4,185 kilograms (9,226 lb)
Gross mass 50,747 kilograms (111,878 lb)
Engines 1 RD-0212
Thrust 613.8 kilonewtons (138,000 lbf)
Specific impulse 325 sec
Burn time 238 seconds
Fuel N2O4/UDMH

The Proton-K, also designated Proton 8K82K after its GRAU index, 8K82K, was a Russian, previously Soviet, carrier rocket derived from the earlier Proton. It was built by Khrunichev, and launched from sites 81 and 200 at the Baikonur Cosmodrome in Kazakhstan.

The maiden flight on 10 March 1967 carried a Soyuz 7K-L1 as part of the Zond program. During the so-called "Moon Race" these Proton/Soyuz/Zond flights consisted of several uncrewed test flights of Soyuz spacecraft to highly elliptical or circumlunar orbits with the unrealized aim of landing Soviet cosmonauts on the Moon.

It was retired from service in favour of the modernised Proton-M, making its 311th and final launch on 30 March 2012.

Vehicle description[edit]

The baseline Proton-K was a three-stage rocket. Thirty were launched in this configuration, with payloads including all of the Soviet Union's Salyut space stations, all Mir modules with the exception of the Docking Module, which was launched on the US Space Shuttle, and the Zarya and Zvezda modules of the International Space Station. It was intended to launch the manned TKS spacecraft, prior to the cancellation of that programme.

The early Proton-K launch configurations from 1965 to 1971

Like other members of the Universal Rocket family, the Proton-K was fuelled by Unsymmetrical dimethylhydrazine and nitrogen tetroxide. These were hypergolic fuels which burn on contact, avoiding the need for an ignition system, and can be stored at ambient temperatures. This avoids the need for low-temperature–tolerant components, and allowed the rocket to sit on the pad fully fuelled for long periods of time. In contrast, cryogenic fuels would have required periodic topping-up of propellants as they boil off. The fuels used on the Proton, were, however, corrosive and toxic and required special handling. The Russian Government paid for the cleanup of residual propellent in spent stages that impact downrange.

Proton components were built in facilities near Moscow, then transported by rail to the final assembly point near the pad. The first stage of the Proton-K consisted of a central oxidiser tank, and six outrigger fuel tanks. This separated as one piece from the second stage, which was attached by means of a lattice structure interstage. The second stage ignited prior to first stage separation, and the top of the first stage was insulated to ensure that it retained its structural integrity until separation.

The first stage used six RD-253 engines, designed by Valentin Glushko. The RD-253 is a single-chamber engine and uses a staged combustion cycle. The first-stage guidance system was open-loop, which required significant amounts of propellant to be held in reserve.

The third stage was powered by an RD-0210 engine and four vernier nozzles, with common systems. The verniers provided steering, eliminating the need for gimballing of the main engine. They also aided stage separation, and acted as ullage motors. Ducts built into the structure channelled vernier exhaust before stage separation. The third stage guidance system was also used to control the first and second stages earlier in flight.

Many launches used an upper stage to boost the payload into a higher orbit. Blok D upper stages were used on forty flights, the majority of which were for the Luna and Zond programmes. Ten flights used the Blok D-1, mostly to launch spacecraft towards Venus. Blok D-2 upper stages were used three times, with the Fobos 1, Fobos 2 and Mars 96 spacecraft. The Blok DM upper stage was used on 66 launches. The most commonly used upper stage was the Blok DM-2, which was used on 109 flights, mostly with GLONASS and Raduga satellites. Fifteen launches used the modernised Block DM-2M stage, mostly carrying Ekspress satellites, however other satellites, including Eutelsat's SESAT 1, also used this configuration. Two Araks satellites were launched using Block DM-5 upper stages. The Block DM1, a commercial version of the DM-2, was used to launch Inmarsat-3 F2. The Block DM2 upper stage was used to launch three groups of seven Iridium satellites, including Iridium 33. This configuration was also used to launch Integral for the European Space Agency. Block DM3 stages were used on twenty five launches, almost exclusively carrying commercial satellites. Telstar 5 was launched with a Block DM4. The Briz-M upper stage was used for four launches; three carrying payloads for the Russian Government, and one commercial launch with GE-9 for GE Americom.[2] One launch was reported to have used a Block DM-3 upper stage, however this may have been a reporting error, and it is unclear whether this launch actually used a DM-3, DM3, or DM-2.

Launch failures[edit]

Source[3]
Flight number Date (UMC) Vehicle model Payload Payload mass, kg Orbit (intended) Orbit (actual) Notes
7 September 27, 1967 Proton K/D Zond 5375 Moon ? One first-stage engine did not start at liftoff due to a rubber plug accidentally left inside during assembly, causing control to gradually fail during ascent. The cutoff command was issued at T+97 seconds and the booster crashed downrange, but the LES pulled the Zond descent module to safety.
8 November 22, 1967 Proton K/D Zond 5375 Moon no One second-stage engine failed to ignite at staging. The remaining three engines were shut down automatically and the booster crashed downrange. Once again, the LES pulled the capsule away to safety. Cause was determined to be premature release of fuel into the second stage, resulting in overheating and engine failure.
10 April 22, 1968 Proton K/D Zond 5375 Moon ? A malfunction in the LES accidentally shut down the second stage at T+260 seconds and triggered an abort. The capsule was successfully recovered.
14 January 20, 1969 Proton K/D Zond 5375 Moon no Second stage turbopump failure at T+313 seconds. The LES once again lifted the Zond capsule to safety.
15 February 19, 1969 Proton K/D Luna probe 2718 Moon no First stage engine failure at T+51 seconds. The booster crashed 15 km from the pad.
16 March 27, 1969 Proton K/D Mars probe 4650 Heliocentric ? Payload fairing collapse at T+51 seconds. The Mars probe was stripped from the booster and the third stage suffered damage, as a result of which it failed to ignite following second stage separation.
17 April 02, 1969 Proton K/D Mars probe 4650 Heliocentric ? A fire in one of the first stage engines caused an almost immediate control loss at liftoff. The booster reached an altitude of 50 km and began flying horizontally before the cutoff command was issued, causing it to plunge nose-first into the ground. Launch complex personnel were unable to leave the Baikonour Cosmodrome due to one exit being blocked by the still-intact second stage and the other by a large puddle of nitrogen tetroxide. They had no choice but to remain there until a rain came and washed the spilled fuel away.
18 June 14, 1969 Proton K/D Luna probe 2718 Moon ? Blok D stage failed to ignite and the probe reentered the atmosphere
18 September 23, 1969 Proton K/D Luna probe  ? Moon ? Blok D LOX valve failure. The probe remained in LEO until reentering.
18 October 22, 1969 Proton K/D Luna probe  ? Moon ? Blok D control malfunction. Probe failed to leave LEO.
23 November 28, 1969 Proton K/D Soyuz  ?  ? ? Pressure sensor malfunction caused first stage cutoff at T+128 seconds
24 February 06, 1970 Proton K/D Luna 5600 Moon no At T+128.3 s, flight safety system automatically shut off first-stage engine because of false alarm from pressure gauge.
30 May 10, 1971 Proton K/D Kosmos 419 4650 Heliocentric LEO Block D flight sequencer programmed incorrectly, resulting in failure to perform second burn or payload separation. Reportedly the coast time between burns was set to 1.5 years instead of 1.5 hours.
36 July 29, 1972 Proton K DOS-2 18000 LEO no At T+181.9 d second-stage stabilization system failed because of short circuit in pitch and yaw channels of the automated stabilization system.
53 October 16, 1975 Proton K/D Luna  ? Moon LEO Failure of fourth-stage oxidizer booster pump.
62 August 04, 1977 Proton K  ?  ? At T+41.1 s, a first-stage engine steering unit failed, causing loss of stability and automatic thrust termination at T+53.7 s.
66 May 27, 1978 Proton K/DM Ekran 1970 GEO no Vehicle stability loss at T+87 s because of an error in first-stage No. 2 engine steering unit. Fault attributed to fuel leak in second-stage engine compartment, which caused control cables to overheat.
68 August 17, 1978 Proton K/DM Ekran 1970 GEO no Loss of stability at T+259.1 s caused flight termination. Hot gas leak from second-stage engine because of faulty seal on pressure gauge led to failure of electrical unit for automatic stabilization.
71 October 17, 1978 Proton K/DM Ekran 1970 GEO no At T+235.62 s, second-stage engine shut off with resultant loss of stability caused by a turbine part igniting in turbo pump gas tract followed by gas inlet destruction and hot air ejection into second rear section.
72 December 19, 1978 Proton K/DM Gorizont 1 1970 GEO GEO, inclination 11.0 Block DM was misaligned for GEO injection burn, resulting in non-circular orbit with 11 deg. inclination
95 July 22, 1982 Proton K/DM Ekran 1970 GEO no First-stage engine No. 5 suffered failure of hydraulic gimbal actuator because of dynamic excitation at T+45 s. Automatic flight shutdown commanded. This would be the last first-stage malfunction of a Proton until 2013.
100 December 24, 1982 Proton K/DM Raduga 1965 GEO no Second-stage failure due to high-frequency vibration.
144 November 29, 1986 Proton K  ?  ? no Second-stage failure.
145 January 30, 1987 Proton K/DM-2 Kosmos-1817 1965 incorrect LEO Fourth stage failed to start because of control system component failure.
148 April 24, 1987 Proton K/DM-2 Kosmos 1838-1840 (Glonass) 3x1260 MEO LEO Fourth stage shut down early and failed to restart. Failure occurred in control system because of manufacturing defect in instrument.
158 January 18, 1988 Proton K/DM-2 Gorizont 2500 GEO no Third-stage engine failure caused by destruction of fuel line leading to mixer.
159 February 17, 1988 Proton K/DM-2 Kosmos 1917-1919 (Glonass) 3x1260 MEO, inclination 64.8 no Fourth-stage engine failure because of high combustion chamber temperatures caused by foreign particles from propellant tank.
187 August 09, 1990 Proton K/DM-2 Ekran M  ? GEO no Second-stage engine shutoff because of termination of oxidizer supply due to fuel line being clogged by a wiping rag.
212 May 27, 1993 Proton K/DM-2 Gorizont 2500 GEO no Second- and third-stage engines suffered multiple burn-throughs of combustion chambers because of propellant contamination.
237 February 19, 1996 Proton K/DM-2 Raduga 33 1965 GTO no Block DM-2 stage failed at ignition for second burn. Suspected causes were failure of a tube joint, which could cause a propellant leak, or possible contamination of hypergolic start system.
243 November 16, 1996 Proton K/D-2 Mars 96 6825 Heliocentric too low LEO Block D-2 fourth-stage engine failed to reinite to boost spacecraft into desired transfer orbit; injection burn did not propel spacecraft out of Earth orbit. Spacecraft and upper stage reentered after a few hours. Root cause could not be determined because of lack of telemetry coverage, but suspected cause was failure of Mars 96 spacecraft, which was controlling Block D stage, or poor integration between spacecraft and stage.
252 December 24, 1997 Proton K/DM3 PAS 22 3410 GTO inclined GTO Block DM shut down early because of improperly coated turbopump seal, leaving spacecraft in high-inclination geosynchronous transfer orbit. Customer declared spacecraft a total loss and collected insurance payment. However, Hudhes salvaged the spacecraft using spacecraft thrusters to raise orbit apogee to perform two lunar swingbys, which lowered inclination and raised perigee. Apogee was then lowered to achieve a geosynchronous orbit inclined 8 deg. Spacecraft has become available for limited use.
265 July 05, 1999 Proton K/Briz-M Raduga 1-5 1965 GTO no Maiden flight of Breeze-M upper stage. Contaminants from welding defect in the turbopump caused the second-stage engine No. 3 to catch fire, destroying the rear section of the stage.
268 October 27, 1999 Proton K/DM-2 Ekspress 1A 2600 GEO no Articulate contamination caused the turbine exhaust duct of second stage engine No. 1 to catch fire at T+223 s, resulting in rapid shutdown of the stage. This and the previous failure in July were attributed to poor workmanship at the Voronezh engine plant. Both engines were part of the same batch built in 1993, during a period when production decreased significantly.
295 November 26, 2002 Proton K/DM3 Astra 1K 2250 GTO no A failed valve caused excess fuel to collect in the Block DM main engine during the parking orbit coast phase after the first burn. The engine was destroyed.

See also[edit]

References[edit]

  1. ^ McDowell, Jonathan. "Proton". Orbital and Suborbital Launch Database. Jonathan's Space Page. 
  2. ^ Krebs, Gunter. "Proton". Gunter's Space Page. 
  3. ^ International reference guide to space launch systems, Fourth Edition, pp. 308-314, ISBN 1-56347-591-X