Proton-M: Difference between revisions

	Proton-M rocket being transported to its launchpad
Function	Heavy carrier rocket
Manufacturer	Khrunichev
Country of origin	Russia
Size
Height	53 metres (174 ft)
Diameter	7.4 metres (24 ft)
Mass	712,800 kilograms (1,571,500 lb)
Stages	3 or 4
Capacity
Payload to LEO
Mass	22,000 kilograms (49,000 lb)
Payload to GTO (Briz-M)
Mass	6,000 kilograms (13,000 lb)
Payload to GSO (Briz-M)
Mass	3,500 kilograms (7,700 lb)
Associated rockets
Family	Universal Rocket
Launch history
Status	Active
Launch sites	Baikonur Sites 81 & 200
Total launches	34
Success(es)	30
Failure(s)	3
Partial failure(s)	1
First flight	7 April 2001
First stage
Height	21 metres (69 ft)
Diameter	7.4 metres (24 ft)
Empty mass	31,000 kilograms (68,000 lb)
Gross mass	450,400 kilograms (993,000 lb)
Powered by	6 RD-253-14D14
Maximum thrust	10,532 kilonewtons (2,368,000 lbf)
Specific impulse	285 sec
Burn time	108 seconds
Propellant	N2O4/UDMH
Second stage – 8S811K
Height	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)
Powered by	4 RD-0210
Maximum thrust	2,399 kilonewtons (539,000 lbf)
Specific impulse	327 sec
Burn time	206 seconds
Propellant	N2O4/UDMH
Third stage
Height	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)
Powered by	1 RD-0212
Maximum thrust	613.8 kilonewtons (138,000 lbf)
Specific impulse	325 sec
Burn time	238 seconds
Propellant	N2O4/UDMH
Fourth stage (optional) – Briz-M
Height	2.61 metres (8 ft 7 in)
Diameter	4.10 metres (13.5 ft)
Empty mass	2,370 kilograms (5,220 lb)
Gross mass	22,170 kilograms (48,880 lb)
Powered by	1 S5.98M
Maximum thrust	19.6 kilonewtons (4,400 lbf)
Specific impulse	326 sec
Burn time	3000 seconds
Propellant	N2O4/UDMH
Fourth stage (optional) – Block DM-2
Powered by	1 RD-58M
Maximum thrust	85 kilonewtons (19,000 lbf)
Specific impulse	352 sec
Propellant	RP-1/LOX
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Revision as of 16:07, 5 February 2012

Template:Launching/Proton (Khrunichev)

The Proton-M, (Протон-М) 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 (ILS), and generally use Site 200/39. The first Proton-M launch occurred on 7 April 2001.

==Vehicle description==

description==

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.

Frank McKenna, CEO of ILS, has indicated that in 2010 the Phase III Proton design would become the standard ILS configuration, with the ability to lift 6.15 metric tons to GTO.^[4]

References

^ McDowell, Jonathan. "Proton". Orbital and Suborbital Launch Database. Jonathan's Space Page.
^ Krebs, Gunter. "Proton". Gunter's Space Page.
^ "DIRECTV 10". ILS.
^ "ILS Reaps Reward of Khrunichev Takeover". Satellite Finance. December 2009.

[1] McDowell, Jonathan. "Proton". Orbital and Suborbital Launch Database. Jonathan's Space Page.

[2] Krebs, Gunter. "Proton". Gunter's Space Page.

[3] "DIRECTV 10". ILS.

[4] "ILS Reaps Reward of Khrunichev Takeover". Satellite Finance. December 2009.

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 The '''Proton-M''', (Протон-М) [[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]] (ILS), and generally use Site 200/39. The first Proton-M launch occurred on 7 April 2001.
-[[File:Proton-M Being Readied for Rollout, January 2005.jpg|thumb|Proton-M in assembly building awaiting for rollout]]==Vehicle description==
+==Vehicle description==[[File:Proton-M Being Readied for Rollout, January 2005.jpg|thumb|Proton-M in assembly building awaiting for rollout]] description==[[File:First stage Proton M.jpg|thumb|Proton-M rollout]]
-[[File:First stage Proton M.jpg|thumb|Proton-M rollout]]
 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.

v t e Orbital launch systems
List of orbital launch systems Comparison of orbital launch systems
Current	Angara 1.2 A5 Ariane 6 Atlas V Ceres 1 1S Chollima-1 Electron Falcon 9 Block 5 Falcon Heavy Firefly Alpha Gravity-1 GSLV H-IIA H3 Hyperbola-1 Jielong 1 3 KAIROS^† Kaituozhe 2 Kinetica 1 Kuaizhou 1 1A 11 Long March 2C 2D 2F 3A 3B/E 3C 4B 4C 5 5B 6 6A 7 7A 8 11 11H 12 LVM3 Minotaur I IV V C Nuri OS-M1^† Pegasus XL Proton-M PSLV Qaem 100 Qased Shavit 2 Simorgh SLS Block 1 Soyuz-2 2.1a / STA 2.1b / STB 2-1v SSLV Starship Tianlong-2 Unha Vega C Vulcan Centaur Zhuque 2
In development	Antares 330 Bloostar Cyclone-4M Deca Epsilon S Eris Gravity-2 Hyperbola-2 Irtysh Kuaizhou 21 31 Long March 9 10 Miura 5 MLV Neutron New Glenn New Line 1 NGLV Nova OS-M 2 4 Orbex Prime Pallas-1 Red Dwarf SLS Block 1B Block 2 Soyuz-7 Terran R Tianlong-3 VLM Vega E Zero Zhuque 3 Zuljanah
Retired	Antares 110 120 130^† 230 230+ Ariane 1 2 3 4 5 ASLV Athena I II Atlas B D E/F G H I II III LV-3B SLV-3 Able^† Agena Centaur Black Arrow Conestoga^† Delta A B C D E G J L M N 0100 1000 2000 3000 4000 5000 II III IV IV Heavy Diamant Dnepr Energia Epsilon Europa I^† II^† Falcon 1 Falcon 9 v1.0 v1.1 v1.2 "Full Thrust" Feng Bao 1 GSLV Mk I H-I H-II H-IIB Juno I Juno II Kaituozhe-1 Kosmos original 1 2/2I 3 3M Lambda 4S LauncherOne Long March 1 1D^† 2A 2E 3 3B 4A Mu 4S 3C 3H 3S 3SII V N1^† N-I N-II Naro-1 Paektusan^† Pilot-2^† R-7 Luna Molniya M L Polyot Soyuz original FG L M U U2 Soyuz/Vostok Sputnik Voskhod Vostok L K 2 2M R-29 Shtil' Volna^† Rocket 3 RS1^† Safir 1 1A 1B Saturn I IB V Scout X-1 Blue Scout II^† X-2^† X-2M X-3 X-3M X-4 X-2B^† B A B-1 D-1 A-1 E-1 F-1 G-1 Shavit original 1 SLV Space Shuttle SPARK^† Sparta SS-520 Start-1 Terran 1^† Thor Able Ablestar 1 2 Agena A B D Burner 1 2 Delta DSV-2U Thorad-Agena SLV-2G SLV-2H Titan II GLV IIIA IIIB IIIC IIID IIIE 34D 23G CT-3 IV Tsyklon R-36-O original 2 3 Universal Rocket UR-500 Proton Proton-K Rokot Strela Vanguard Vega original VLS-1^† Zenit 2 2M 2FG 3SL 3SLB 3F Zhuque 1^†
Classes	Sounding rocket Small-lift launch vehicle Medium-lift launch vehicle Heavy-lift launch vehicle Super heavy-lift launch vehicle
This Template lists historical, current, and future space rockets that at least once attempted (but not necessarily succeeded in) an orbital launch or that are planned to attempt such a launch in the future Symbol ^† indicates past or current rockets that attempted orbital launches but never succeeded (never did or has yet to perform a successful orbital launch)

v t e Soviet and Russian launch vehicles
Active	Angara 1.2 A5 Soyuz-2 2.1a 2.1b 2-1v UR Proton-M
In development	Amur Irtysh Yenisei
Retired	Dnepr Energia Kosmos 1 2I 3 3M N1 R-7 Luna Molniya M L Polyot Soyuz original L M U U2 FG Soyuz/Vostok Sputnik Voskhod Vostok L K 2 2M R-29 Shtil' Volna Start-1 Tsyklon original 2 3 UR UR-500 Proton-K Rokot Strela Zenit 2 2M 3SL 3SLB 3F
Cancelled (no launch attempts)	Tsyklon-4 Proton Light Medium

Revision as of 16:07, 5 February 2012

Proton-M Enhanced

See also

References