Proton-M: Difference between revisions
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|manufacturer = [[Khrunichev State Research and Production Space Center|Khrunichev]] |
|manufacturer = [[Khrunichev State Research and Production Space Center|Khrunichev]] |
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|image = Mars 96 Proton.jpg |
|image = Mars 96 Proton.jpg |
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|imsize = 150 |
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|function = Heavy carrier rocket |
|function = Heavy carrier rocket |
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|country-origin = {{RUS}} |
|country-origin = {{RUS}} |
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Revision as of 16:24, 8 September 2009
 | |
| 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 | 30 |
| Success(es) | 27 |
| Failure(s) | 2 |
| Partial failure(s) | 1 |
| First flight | 7 April 2001[1] |
| 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 |
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
- ^ McDowell, Jonathan. "Proton". Orbital and Suborbital Launch Database. Jonathan's Space Page.
- ^ Krebs, Gunter. "Proton". Gunter's Space Page.
- ^ "DIRECTV 10" (PDF). Khrunichev.