Proton-M rocket on the launchpad
|Function||Heavy lift launch vehicle|
|Country of origin||Russia|
|Height||58.2 m (191 ft)|
|Diameter||7.4 m (24 ft)|
|Mass||705,000 kg (1,554,000 lb)|
|Stages||3 or 4|
|Payload to LEO[a]||23,000 kg (51,000 lb)|
|Payload to GTO 1800 m/s[b]||6,920 kg (15,260 lb)|
|Payload to GTO 1500 m/s[c]||6,300 kg (13,900 lb)|
|Payload to GSO[d]||3,250 kg (7,170 lb)|
|First flight||7 April 2001|
|Last flight||9 June 2016|
|First stage - 8S810K|
|Length||21.18 m (69.5 ft)|
|Diameter||7.4 m (24 ft)|
|Empty mass||30,600 kg (67,500 lb)|
|Propellant mass||428,300 kg (944,200 lb)|
|Thrust||10,532 kN (2,368,000 lbf)|
|Specific impulse||285 sec|
|Burn time||108 sec|
|Fuel||N2O4 / UDMH|
|Second stage - 8S811K|
|Length||17.05 m (55.9 ft)|
|Diameter||4.1 m (13 ft)|
|Empty mass||11,000 kg (24,000 lb)|
|Propellant mass||157,300 kg (346,800 lb)|
|Thrust||2,399 kN (539,000 lbf)|
|Specific impulse||327 sec|
|Burn time||206 sec|
|Fuel||N2O4 / UDMH|
|Third stage - 8S812|
|Length||4.11 m (13.5 ft)|
|Diameter||4.1 m (13 ft)|
|Empty mass||3,500 kg (7,700 lb)|
|Propellant mass||46,562 kg (102,652 lb)|
|Thrust||613.8 kN (138,000 lbf)|
|Specific impulse||325 sec|
|Burn time||238 sec|
|Fuel||N2O4 / UDMH|
|Fourth stage (optional) - Briz-M|
|Length||2.61 m (8 ft 7 in)|
|Diameter||4.0 m (13.1 ft)|
|Empty mass||2,370 kg (5,220 lb)|
|Propellant mass||19,800 kg (43,700 lb)|
|Thrust||19.62 kN (4,410 lbf)|
|Specific impulse||326 sec|
|Burn time||3000 sec|
|Fuel||N2O4 / UDMH|
|Fourth stage (optional) - Blok DM-2|
|Thrust||85 kN (19,000 lbf)|
|Specific impulse||352 sec|
|Fuel||RP-1 / LOX|
|Fourth stage (optional) - Blok DM-03|
|Fuel||RP-1 / LOX|
The Proton-M, (Протон-М) GRAU index 8K82M or 8K82KM, is a Russian heavy lift launch vehicle derived from the Soviet-developed Proton. It is built by Khrunichev, and launched from sites 81 and 200 at the Baikonur Cosmodrome in Kazakhstan. Commercial launches are marketed by International Launch Services (ILS), and generally use Site 200/39. The first Proton-M launch occurred on 7 April 2001.
The Proton-M launch vehicle consists of 3 stages; all of them powered by liquid fueled engines using the hypergolic propellant combination of dinitrogen tetroxide as the oxidizer, and unsymmetrical dimethylhydrazine for fuel (see infobox).
The first stage is unique in that it consists of a central cylindrical oxidizer tank with the same diameter as the other 2 stages with 6 fuel tanks attached to its circumference, each carrying an engine. The engines in this stage can swivel tangentially up to 7° from the neutral position, providing full thrust vector control. The rationale for this design is logistics: the diameter of the oxidizer tanks and the 2 following stages is the maximum that can be delivered by railroad to Baikonur. However, within Baikonur the fully assembled stack is transported again by rail, as it has enough clearance.
The second stage uses a conventional cylindrical design. It is powered by 3 RD-0210 engine and 1 RD-0211 engine. The RD-0211 is a modified version of the RD-0210 used to pressurize the propellant tanks. The second stage is joined to the first stage through a net instead of a closed inter-stage, to allow the exhaust to escape because the second stage begins firing seconds before separation. Thrust vector control is provided by engine gimballing.
The third stage is also of a conventional cylindrical design. It contains the avionics system that controls the first 3 stages. It uses 1 RD-0213 which is a fixed (non-gimballed) version of the RD-0210, and 1 RD-0214 which is a 4 nozzle vernier engine used for thrust vector control. The nozzles of the RD-0214 can turn up to 45°; they are placed around (with some separation), and moderately above the nozzle of the RD-0213.
The Proton-M features modifications to the lower stages to reduce structural mass, increase thrust, and utilise more propellant (less of it remains unused in the tanks). A closed-loop guidance system is used on the first stage, which allows more complete consumption of propellant. This increases the rocket's performance slightly compared to previous variants, and reduces the amount of toxic chemicals remaining in the stage when it impacts downrange. It can place up to 21 tonnes (46,000 lb) into low Earth orbit. With an upper stage, it can place a 3 tonne payload into geosynchronous orbit, or a 5.5 tonne payload into geosynchronous transfer orbit. Efforts were also made to reduce dependency on foreign component suppliers.
Most Proton-M launches have used a Briz-M upper stage to propel the spacecraft into a higher orbit. Launches have also been made with Blok-DM upper stages: six launches were made with the Blok DM-2 upper stage carrying GLONASS spacecraft, while two further GLONASS launches have used the Blok DM-03. The DM-03 will be used for a total of five launches; a further GLONASS launch is planned along with two launches of Ekspress satellites. As of 2013, no Proton-M launches have been made without an upper stage. However, this configuration is manifested to launch the Multipurpose Laboratory Module and European Robotic Arm of the International Space Station, currently scheduled to be launched together in 2017.
- PLF-BR-13305 short faring.
- PLF-BR-15255 long faring.
Both fairings have a diameter of 4.35 m.
On 7 July 2007, International Launch Services launched the first Proton-M Enhanced rocket, which carried the DirecTV-10 satellite into orbit. This was the 326th launch of a Proton, the 16th Proton-M/Briz-M launch, and the 41st Proton launch to be conducted by ILS. It features more efficient first stage engines, updated avionics, lighter fuel tanks and more powerful vernier engines on the Briz-M upper stage, and mass reduction throughout the rocket, including thinner fuel tank walls on the first stage, and use of composite materials on all other stages. The second launch of this variant occurred on 18 August 2008, and was used to place Inmarsat 4 F3 into orbit. The baseline Proton-M was retired in November 2007, in favour of the Enhanced variant.
In a typical mission, a Proton-M is accompanied by a Briz-M upper stage. The Proton-M launches the orbital unit (that is: the payload, the payload adapter and the Briz-M) into a slightly suborbital trajectory. The first and second stages and the payload fairing crash into designated crash sites; the third stage crashes into the ocean. After the third stage separates, the orbital unit coasts for a brief period, then Briz-M performs its first firing to achieve orbital injection into a parking orbit with 51.5° inclination, at 170 km to 230 km altitude (the Mission Planner's Guide also mentions 64.8° and 72.6° as standard inclinations for the parking orbit). Subsequently the Briz-M performs orbital maneuvers to place the payload into either its final orbit or a transfer orbit. If a transfer orbit is used the final maneuver(s) are performed by the payload on its own propulsion system.
As of May 2015[update] more than 100 Proton-M launches have occurred, of which 10 have failed. Three of these failures were the results of problems with the Proton-M itself, six were caused by the Briz-M upper stage malfunctioning and leaving cargo in a useless orbit, and one was the result of a Blok DM-03 upper stage being incorrectly fuelled, leaving the Proton too heavy to achieve orbit.
In September 2007, a Proton-M/Briz-M rocket carrying Japan's JCSAT-11 communications satellite failed to achieve orbit, and fell in the Ulytau District of Kazakhstan. An investigation determined that first and second stages of the rocket had failed to separate, due to a damaged pyrotechnic cable.
In July 2013, a Proton-M/DM-03 carrying three GLONASS satellites failed shortly after liftoff. The booster began pitching left and right along the vertical axis within a few seconds of launch. Attempts by the onboard guidance computer to correct the flight trajectory failed and ended up putting it into an unrecoverable pitchover. The upper stages and payload were stripped off 24 seconds after launch due to the forces experienced followed by the first stage breaking apart and erupting in flames. Impact with the ground occurred 30 seconds after liftoff.
The preliminary report of the investigation indicated that three of the first stage angular velocity sensors, responsible for yaw control, were installed in an incorrect orientation. As the error affected the redundant sensors as well as the primary ones, the rocket was left with no yaw control, which resulted in the failure. Telemetry data also indicated that a pad umbilical had detached prematurely, suggesting that the Proton may have launched several tenths of a second early, before the engines reached full thrust.
In May 2014, another Proton-M launch ended in failure, resulting in the loss of an Ekspress telecommunications satellite. Unlike the 2013 disaster, this occurred more than nine minutes into the flight when one of the third stage verniers shut off, causing loss of attitude control. An automatic shutdown and destruct command was issued and the remains of the upper stages and payload landed in northern China. An investigation committee concluded that the failure was most likely due to one of the turbopumps breaking off its mount, rupturing a propellant line and causing the vernier to lose thrust.
In May 2015, a Proton-M with a Mexican telecommunications satellite was lost due to problems with the third stage. Russian sources indicated that the problems had been the same as with the 2014 failure.
Although other Proton-M launches are recorded as failures, these failures have been caused by the upper stages used to allow the rocket to deliver payloads to higher orbits. On 5 December 2010, the upper stage and payloads failed to reach orbital velocity due to overloading of the upper stage with 1.5 tonnes of liquid oxygen, resulting in the loss of three GLONASS satellites it was carrying.
Five launches have succumbed to problems with the Briz-M upper stage; Arabsat 4A in February 2006, AMC-14 in March 2008, Ekspress-AM4 in August 2011, Telkom 3 and Ekspress-MD2 in August 2012 and Yamal 402 in December 2012. All of the payloads were unusable except for Yamal 402, which was able to correct its orbit at the expense of several years' operational life, and AMC-14 which was sold to the US Government after SES determined that it couldn't complete its original mission.
Effect on government and industry
As a result of the July 2013 Proton M launch, a major reorganization of the Russian space industry was undertaken. The United Rocket and Space Corporation was formed as a joint-stock corporation by the government in August 2013 to consolidate the Russian space sector. Deputy Prime Minister Dmitry Rogozin said "the failure-prone space sector is so troubled that it needs state supervision to overcome its problems." Three days following the failure, the Russian government had announced that "extremely harsh measures" would be taken "and spell the end of the [Russian] space industry as we know it."
Critics claim that Proton rocket fuel (unsymmetrical dimethylhydrazine (UDMH)) and debris created by Russia's space programme is poisoning areas of Russia and Kazakhstan. Residents claim that acid rain falls after some launches. Anatoly Kuzin, deputy director of the Khrunichev State Research and Production Space Center, has however denied these claims, saying: "We did special research into the issue. The level of acidity in the atmosphere is not affected by the rocket launches [and] there is no data to prove any link between the illnesses [in Altai] and the influence of rocket fuel components or space activity of any kind".
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