Proton-K: Difference between revisions
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The '''Proton-K''', also designated '''Proton 8K82K''' after its [[GRAU index]], '''8K82K''', is a [[Russia]]n, previously [[Soviet Union|Soviet]], [[launch vehicle|carrier rocket]] derived from the earlier [[Proton (rocket)|Proton]]. It was built by [[Khrunichev State Research and Production Space Center|Khrunichev]], and is launched from sites [[Baikonur Cosmodrome Site 81|81]] and [[Baikonur Cosmodrome Site 200|200]] at the [[Baikonur Cosmodrome]] in [[Kazakhstan]]. As of 2009, it is out of production, with approximately three launches remaining prior to its retirement in favour of the modernised [[Proton-M]]. |
The '''Proton-K''', also designated '''Proton 8K82K''' after its [[GRAU index]], '''8K82K''', is a [[Russia]]n, previously [[Soviet Union|Soviet]], [[launch vehicle|carrier rocket]] derived from the earlier [[Proton (rocket)|Proton]]. It was built by [[Khrunichev State Research and Production Space Center|Khrunichev]], and is launched from sites [[Baikonur Cosmodrome Site 81|81]] and [[Baikonur Cosmodrome Site 200|200]] at the [[Baikonur Cosmodrome]] in [[Kazakhstan]]. As of 2009, it is out of production, with approximately three launches remaining prior to its retirement in favour of the modernised [[Proton-M]]. |
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==Vehicle description== [[File:Early Proton-K rocket versions.jpg|thumb|The early Proton-K launch configurations from 1965 to 1971]] |
==Vehicle description== |
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[[File:Early Proton-K rocket versions.jpg|thumb|The early Proton-K launch configurations from 1965 to 1971]] |
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The baseline Proton-K is a three-stage rocket. Thirty have been launched in this configuration, with payloads including all of the Soviet Union's [[Salyut program|''Salyut'']] [[space stations]], all [[Mir]] modules with the exception of the [[Mir Docking Module|Docking Module]], which was launched on the [[United States|US]] [[Space Shuttle]], and the [[Zarya]] and [[Zvezda (ISS module)|Zvezda]] modules of the [[International Space Station]]. It was intended to launch the manned [[TKS spacecraft]], prior to the cancellation of that programme. |
The baseline Proton-K is a three-stage rocket. Thirty have been launched in this configuration, with payloads including all of the Soviet Union's [[Salyut program|''Salyut'']] [[space stations]], all [[Mir]] modules with the exception of the [[Mir Docking Module|Docking Module]], which was launched on the [[United States|US]] [[Space Shuttle]], and the [[Zarya]] and [[Zvezda (ISS module)|Zvezda]] modules of the [[International Space Station]]. It was intended to launch the manned [[TKS spacecraft]], prior to the cancellation of that programme. |
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Revision as of 17:07, 5 February 2012
 Launch of a Proton-K with Zarya | |
| Function | Heavy carrier rocket |
|---|---|
| Manufacturer | Khrunichev |
| Country of origin |  Soviet Union Russia |
| Size | |
| Height | 50 metres (160 ft) |
| Diameter | 7.4 metres (24 ft) |
| Stages | 3 or 4 |
| Associated rockets | |
| Family | Universal Rocket |
| Launch history | |
| Status | Out of production |
| Launch sites | Baikonur Sites 81 & 200 |
| First flight | 10 March 1967[1] |
| First stage | |
| Height | 21.2 metres (70 ft) |
| Diameter | 7.4 metres (24 ft) |
| Empty mass | 31,100 kilograms (68,600 lb) |
| Gross mass | 450,510 kilograms (993,200 lb) |
| Powered by | 6 RD-253-14D48 |
| Maximum thrust | 10,470 kilonewtons (2,350,000 lbf) |
| Specific impulse | 316 sec |
| Burn time | 124 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 |
The Proton-K, also designated Proton 8K82K after its GRAU index, 8K82K, is a Russian, previously Soviet, carrier rocket derived from the earlier Proton. It was built by Khrunichev, and is launched from sites 81 and 200 at the Baikonur Cosmodrome in Kazakhstan. As of 2009, it is out of production, with approximately three launches remaining prior to its retirement in favour of the modernised Proton-M.
Vehicle description
The baseline Proton-K is a three-stage rocket. Thirty have been launched in this configuration, with payloads including all of the Soviet Union's Salyut space stations, all Mir modules with the exception of the Docking Module, which was launched on the US Space Shuttle, and the Zarya and Zvezda modules of the International Space Station. It was intended to launch the manned TKS spacecraft, prior to the cancellation of that programme.
It is fuelled by Unsymmetrical dimethylhydrazine and nitrogen tetroxide. These are hypergolic fuels which burn on contact, avoiding the need for an ignition system, and can be stored at ambient temperatures. This avoids the need for low-temperature–tolerant components, and allows the rocket to sit on the pad fully fuelled for long periods of time. In contrast, cryogenic fuels need periodic topping-up of propellants as they boil off. The fuels used on the Proton, are, however, corrosive and toxic and require special handling. The Russian Government pays for the cleanup of residual propellent in spent stages that impact downrange.
Proton components were built in facilities near Moscow, then transported by rail to the final assembly point near the pad. The first stage of the Proton-K consists of a central oxidiser tank, and six outrigger fuel tanks. This separates as one piece from the second stage, which is attached by means of a lattice structure interstage. The second stage ignites prior to first stage separation, and the top of the first stage is insulated to ensure that it retains its structural integrity until separation.
The first stage uses six RD-253 engines, designed by Valentin Glushko. The RD-253 is a single-chamber engine and uses a staged combustion cycle. The first-stage guidance system is open-loop, which requires significant amounts of propellant to be held in reserve.
The third stage is powered by an RD-0210 engine and four vernier nozzles, with common systems. The verniers provide steering, eliminating the need for gimballing of the main engine. They also aid stage separation, and act as ullage motors. Ducts are built into the structure to channel vernier exhaust before stage separation. The third stage guidance system is also used to control the first and second stages flight.
Many launches have used an upper stage to boost the payload into a higher orbit. Block D upper stages were used on forty flights, the majority of which were for the Luna and Zond programmes. Ten flights used the Block D-1, mostly to launch spacecraft towards Venus. Block D-2 upper stages were used three times, with the Fobos 1, Fobos 2 and Mars 96 spacecraft. The Block DM upper stage was used on 66 launches. The most commonly used upper stage is the Block DM-2, which has been used on 107 flights, mostly with GLONASS and Raduga satellites. Fifteen launches have used the modernised Block DM-2M stage, mostly carrying Ekspress satellites, however other satellites, including Eutelsat's SESAT 1, have also used this configuration. Two Araks satellites were launched using Block DM-5 upper stages. The Block DM1, a commercial version of the DM-2, was used to launch Inmarsat-3 F2. The Block DM2 upper stage was used to launch three groups of seven Iridium satellites, including Iridium 33. This configuration was also used to launch Integral for the European Space Agency. Block DM3 stages were used on twenty five launches, almost exclusively carrying commercial satellites. Telstar 5 was launched with a Block DM4. The Briz-M upper stage was used for four launches; three carrying payloads for the Russian Government, and one commercial launch with GE-9 for GE Americom.[2] One launch was reported to have used a Block DM-3 upper stage, however this may have been a reporting error, and it is unclear whether this launch actually used a DM-3, DM3, or DM-2.