Proton-K

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Due to its rushed development, the Proton K launch vehicle had a low success rate initially. However, the issues were rectified and it went on to become one of the most widely used heavy launch vehicle.

Launch failures

Proton Zvezda crop.jpg
Launch of a Proton-K carrying the Zvezda module of the International Space Station
Function Heavy-lift launch vehicle
Manufacturer Khrunichev
Country of originUSSR
Russia
Size
Height50 metres (160 ft)
Diameter7.4 metres (24 ft)
Stages3 or 4
Capacity
Payload to LEO
Mass19,760 kg (43,560 lb)
Record: 22,776 kg (50,212 lb) with Zvezda [1]
Associated rockets
Family Universal Rocket
Derivative work Proton-M
Launch history
StatusRetired
Launch sites Baikonur Sites 81 & 200
Total launches310
Success(es)275 (89%)
Failure(s)24
Partial failure(s)11
First flight10 March 1967 [2]
Last flight30 March 2012
First stage
Height21.2 metres (70 ft)
Diameter7.4 metres (24 ft)
Empty mass31,100 kilograms (68,600 lb)
Gross mass450,510 kilograms (993,200 lb)
Powered by6 RD-253-14D48
Maximum thrust10,470 kilonewtons (2,350,000 lbf)
Specific impulse 316 sec
Burn time124 seconds
Propellant N2O4/UDMH
Source [4]
Flight numberDate (UMC)Vehicle modelPayloadPayload mass, kgOrbit (intended)Orbit (actual)Notes
7September 27, 1967Proton K/DZond5375Moon?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 Launch Escape System (LES) pulled the Zond descent module to safety.
8November 22, 1967Proton K/DZond5375MoonnoOne 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.
10April 22, 1968Proton K/DZond5375Moon?A malfunction in the LES accidentally shut down the second stage at T+260 seconds and triggered an abort. The capsule was successfully recovered.
14January 20, 1969Proton K/DZond5375MoonnoSecond stage turbopump failure at T+313 seconds. The LES once again lifted the Zond capsule to safety.
15February 19, 1969Proton K/DLuna probe2718MoonnoPayload fairing collapsed at T+51 seconds. Flying debris ruptured the first stage and caused leaking propellant to ignite on contact with the engine exhaust, resulting in the explosion of the launch vehicle.
16March 27, 1969Proton K/DMars probe4650 Heliocentric ?Third stage turbopump failure at T+438 seconds. The upper stages and payload crashed in the Altai mountains.
17April 2, 1969Proton K/DMars probe4650 Heliocentric ?A fire in one of the first stage engines caused an almost immediate control loss at liftoff. The booster reached an altitude of 300m 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.
18June 14, 1969Proton K/DLuna probe2718Moon?Blok D stage failed to ignite and the probe reentered the atmosphere
18September 23, 1969Proton K/DLuna probe ?Moon?Blok D LOX valve failure. The probe remained in LEO until reentering.
18October 22, 1969Proton K/DLuna probe ?Moon?Blok D control malfunction. Probe failed to leave LEO.
23November 28, 1969Proton K/DSoyuz ? ??Pressure sensor malfunction caused first stage cutoff at T+128 seconds
24February 6, 1970Proton K/DLuna5600MoonnoAt T+128.3 s, flight safety system automatically shut off first-stage engine because of false alarm from pressure gauge.
30May 10, 1971Proton 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.
36July 29, 1972Proton K DOS-2 18000 LEO noAt T+181.9 d second-stage stabilization system failed because of short circuit in pitch and yaw channels of the automated stabilization system.
53October 16, 1975Proton K/DLuna ?Moon LEO Failure of fourth-stage oxidizer booster pump.
62August 4, 1977Proton KAlmaz ? LEO noAt T+41.1 s, a first-stage engine steering unit failed, causing loss of stability and automatic thrust termination at T+53.7 s.
66May 27, 1978Proton K/DMEkran1970 GEO noVehicle 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.
68August 17, 1978Proton K/DMEkran1970 GEO noLoss 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.
71October 17, 1978Proton K/DMEkran1970 GEO noAt T+235.62 s, second-stage engine shut off with resultant loss of stability caused by a turbine part igniting in turbopump gas tract followed by gas inlet destruction and hot air ejection into second rear section.
72December 19, 1978Proton K/DMGorizont 11970 GEO GEO, inclination 11.0Block DM was misaligned for GEO injection burn, resulting in non-circular orbit with 11 deg. inclination
95July 22, 1982Proton K/DMEkran1970 GEO noFirst-stage engine No. 5 suffered failure of hydraulic gimbal actuator because of dynamic excitation at T+45 seconds. Automatic flight shutdown commanded. This would be the last first-stage malfunction of a Proton until 2013.
100December 24, 1982Proton K/DMRaduga1965 GEO noSecond-stage failure T+230 seconds due to high-frequency vibration.
144November 29, 1986Proton KRaduga1965noSecond stage control failure due to an electrical relay becoming separated from vibration
145January 30, 1987Proton K/DM-2 Kosmos-1817 1965incorrect LEO Fourth stage failed to start because of control system component failure.
148April 24, 1987Proton K/DM-2Kosmos 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.
158January 18, 1988Proton K/DM-2Gorizont2500 GEO noThird-stage engine failure caused by destruction of fuel line leading to mixer.
159February 17, 1988Proton K/DM-2Kosmos 1917-1919 (Glonass)3x1260 MEO, inclination 64.8noFourth-stage engine failure because of high combustion chamber temperatures caused by foreign particles from propellant tank.
187August 9, 1990Proton K/DM-2Ekran M ? GEO noSecond-stage engine shutoff because of termination of oxidizer supply due to fuel line being clogged by a wiping rag.
212May 27, 1993Proton K/DM-2Gorizont2500 GEO noSecond- and third-stage engines suffered multiple burn-throughs of combustion chambers because of propellant contamination.
237February 19, 1996Proton K/DM-2Raduga 331965 GTO noBlock 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.
243November 16, 1996Proton K/D-2 Mars 96 6825 Heliocentric too low LEO Block D-2 fourth-stage engine failed to reignite 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.
252December 24, 1997Proton 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, Hughes 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.
265July 5, 1999Proton K/Briz-MRaduga 1-51965 GTO noMaiden flight of Briz-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.
268October 27, 1999Proton K/DM-2Ekspress 1A2600 GEO noParticulate 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.
295November 26, 2002Proton K/DM3Astra 1K2250 GTO noA 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

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References

  1. "Zvezda Service Module". Khrunichev . Retrieved June 11, 2017.
  2. McDowell, Jonathan. "Proton". Orbital and Suborbital Launch Database. Jonathan's Space Page.
  3. Krebs, Gunter. "Proton". Gunter's Space Page.
  4. International reference guide to space launch systems, Fourth Edition, pp. 308-314, ISBN   1-56347-591-X