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{{Infobox Rocket
#REDIRECT [[Proton (rocket)]]
|manufacturer = [[Khrunichev State Research and Production Space Center|Khrunichev]]
|function = Heavy carrier rocket
|country-origin = {{RUS}}
|status = Active
|sites = [[Baikonur Cosmodrome|Baikonur]] Sites [[Baikonur Cosmodrome Site 81|81]] & [[Baikonur Cosmodrome Site 200|200]]
|capacities =
{{Infobox Rocket/Payload|location = [[Low Earth orbit|LEO]]|kilos={{convert|21000|kg}}}}
{{Infobox Rocket/Payload|location = [[Geosynchronous transfer orbit|GTO]] (Briz-M)|kilos={{convert|5500|kg}}}}
{{Infobox Rocket/Payload|location = [[Geosynchronous orbit|GSO]] (Briz-M)|kilos={{convert|2920|kg}}}}
|mass = {{convert|712800|kg}}
|height = {{convert|53|m}}
|diameter = {{convert|7.4|m}}
|stages = 3 or 4
|launches = 29
|fail = 2
|partial = 1
|success = 26
|first = 7 April 2001<ref>{{cite web|url=http://planet4589.org/space/lvdb/launch/Proton|title=Proton|work=Orbital and Suborbital Launch Database|first=Jonathan|last=McDowell|publisher=Jonathan's Space Page}}</ref>
|family = [[Universal Rocket]]
|stagedata =
{{Infobox Rocket/Stage
|type = stage
|stageno = First
|engines = 6 [[RD-253|RD-253-14D14]]
|thrust = {{convert|10532|kN}}
|SI = 285 sec
|burntime = 108 seconds
|fuel = [[Dinitrogen tetroxide|N<sub>2</sub>O<sub>4</sub>]]/[[Unsymmetrical dimethylhydrazine|UDMH]]
|length = {{convert|21|m}}
|diameter = {{convert|7.4|m}}
|gross = {{convert|450400|kg}}
|empty = {{convert|31000|kg}}
}}
{{Infobox Rocket/Stage
|type = stage
|stageno = Second
|engines = 4 [[RD-0210]]
|name = 8S811K
|thrust = {{convert|2399|kN}}
|SI = 327 sec
|burntime = 206 seconds
|fuel = N<sub>2</sub>O<sub>4</sub>/UDMH
|length = {{convert|14|m}}
|diameter = {{convert|4.15|m}}
|gross = {{convert|167828|kg}}
|empty = {{convert|11715|kg}}
}}
{{Infobox Rocket/Stage
|type = stage
|stageno = Third
|engines = 1 [[RD-0212]]
|thrust = {{convert|613.8|kN}}
|SI = 325 sec
|burntime = 238 seconds
|fuel = N<sub>2</sub>O<sub>4</sub>/UDMH
|length = {{convert|6.5|m}}
|diameter = {{convert|4.15|m}}
|gross = {{convert|50747|kg}}
|empty = {{convert|4185|kg}}
}}
{{Infobox Rocket/Stage
|type = stage
|stageno = Fourth
|diff = optional
|name = [[Briz-M]]
|engines = 1 [[S5.98M]]
|thrust = {{convert|19.6|kN}}
|SI = 326 sec
|burntime = 3000 seconds
|fuel = N<sub>2</sub>O<sub>4</sub>/UDMH
|length = {{convert|2.61|m}}
|diameter = {{convert|4.10|m}}
|gross = {{convert|22170|kg}}
|empty = {{convert|2370|kg}}
}}
{{Infobox Rocket/Stage
|type = stage
|stageno = Fourth
|diff = optional
|name = [[Block DM-2]]
|engines = 1 [[RD-58M]]
|thrust = {{convert|85|kN}}
|SI = 352 sec
|burntime =
|fuel = [[RP-1]]/[[liquid oxygen|LOX]]
}}
}}
The '''Proton-M''', [[GRAU index]] '''8K82M''' or '''8K82KM''', is a [[Russia]]n [[launch vehicle|carrier rocket]] derived from the [[Soviet Union|Soviet]]-developed [[Proton (rocket)|Proton]]. It is built by [[Khrunichev State Research and Production Space Center|Khrunichev]], and launched from sites [[Baikonur Cosmodrome Site 81|81]] and [[Baikonur Cosmodrome Site 200|200]] at the [[Baikonur Cosmodrome]] in [[Kazakhstan]]. Commercial launches are marketed by [[International Launch Services]], and generally use Site 200/39. The first Proton-M launch occurred on 7 April 2001.

The Proton-M features modifications to the lower stages to reduce structural mass, increase thrust, and fully utilise propellants. 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 lands downrange. It can place up to {{convert|21|t|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 [[Block-DM]] upper stages, namely the Block DM-2 when launching [[GLONASS]] spacecraft, and a scheduled launch with two Yamal satellites, using a Block DM-3.<ref>{{cite web|url=http://space.skyrocket.de/index_frame.htm?http://space.skyrocket.de/doc_lau_fam/proton.htm|title=Proton|first=Gunter|last=Krebs|publisher=Gunter's Space Page}}</ref> As of 2009, 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 [[2011 in spaceflight|2011]].

==Proton-M Enhanced==
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.<ref>{{cite web |url=http://www.khrunichev.ru/khrunichev/upload/images/autoref/DirecTV_10.pdf |format=PDF|title=DIRECTV 10 |publisher=[[Khrunichev]]}}</ref> 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 (satellite)|Inmarsat 4 F3]] into orbit. The baseline Proton-M was retired in November 2007, in favour of the Enhanced variant.

==See also==
*[[Comparison of heavy lift launch systems]]
*[[List of Proton launches]]

==References==
{{reflist}}


{{Expendable launch systems}}
{{Russian launch vehicles}}

Revision as of 19:47, 5 March 2009

FunctionHeavy carrier rocket
ManufacturerKhrunichev
Country of origin Russia
Size
Height53 metres (174 ft)
Diameter7.4 metres (24 ft)
Mass712,800 kilograms (1,571,500 lb)
Stages3 or 4
Capacity
Payload to LEO
Mass21,000 kilograms (46,000 lb)
Payload to GTO (Briz-M)
Mass5,500 kilograms (12,100 lb)
Payload to GSO (Briz-M)
Mass2,920 kilograms (6,440 lb)
Associated rockets
FamilyUniversal Rocket
Launch history
StatusActive
Launch sitesBaikonur Sites 81 & 200
Total launches29
Success(es)26
Failure(s)2
Partial failure(s)1
First flight7 April 2001[1]
First stage
Height21 metres (69 ft)
Diameter7.4 metres (24 ft)
Empty mass31,000 kilograms (68,000 lb)
Gross mass450,400 kilograms (993,000 lb)
Powered by6 RD-253-14D14
Maximum thrust10,532 kilonewtons (2,368,000 lbf)
Specific impulse285 sec
Burn time108 seconds
PropellantN2O4/UDMH
Second stage – 8S811K
Height14 metres (46 ft)
Diameter4.15 metres (13.6 ft)
Empty mass11,715 kilograms (25,827 lb)
Gross mass167,828 kilograms (369,997 lb)
Powered by4 RD-0210
Maximum thrust2,399 kilonewtons (539,000 lbf)
Specific impulse327 sec
Burn time206 seconds
PropellantN2O4/UDMH
Third stage
Height6.5 metres (21 ft)
Diameter4.15 metres (13.6 ft)
Empty mass4,185 kilograms (9,226 lb)
Gross mass50,747 kilograms (111,878 lb)
Powered by1 RD-0212
Maximum thrust613.8 kilonewtons (138,000 lbf)
Specific impulse325 sec
Burn time238 seconds
PropellantN2O4/UDMH
Fourth stage (optional) – Briz-M
Height2.61 metres (8 ft 7 in)
Diameter4.10 metres (13.5 ft)
Empty mass2,370 kilograms (5,220 lb)
Gross mass22,170 kilograms (48,880 lb)
Powered by1 S5.98M
Maximum thrust19.6 kilonewtons (4,400 lbf)
Specific impulse326 sec
Burn time3000 seconds
PropellantN2O4/UDMH
Fourth stage (optional) – Block DM-2
Powered by1 RD-58M
Maximum thrust85 kilonewtons (19,000 lbf)
Specific impulse352 sec
PropellantRP-1/LOX
[edit on Wikidata]

The Proton-M, GRAU index 8K82M or 8K82KM, is a Russian carrier rocket 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, and generally use Site 200/39. The first Proton-M launch occurred on 7 April 2001.

The Proton-M features modifications to the lower stages to reduce structural mass, increase thrust, and fully utilise propellants. 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 lands 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 Block-DM upper stages, namely the Block DM-2 when launching GLONASS spacecraft, and a scheduled launch with two Yamal satellites, using a Block DM-3.[2] As of 2009, 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 2011.

Proton-M Enhanced

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.[3] 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.

See also

References

  1. ^ McDowell, Jonathan. "Proton". Orbital and Suborbital Launch Database. Jonathan's Space Page.
  2. ^ Krebs, Gunter. "Proton". Gunter's Space Page.
  3. ^ "DIRECTV 10" (PDF). Khrunichev.


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