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|mass = |height = |diameter = |stages = 3 or 4 |launches = 117 〔(Another Disaster for Russia’s Space Workhorse ), ''Popular Mechanics'', 16 May 2014, accessed 16 May 2014.〕 |fail = 8 |partial = 3 |success = 106 |first = 7 April 2001 |family = Universal Rocket |stagedata = }} The Proton-M, (Протон-М) GRAU index 8K82M or , 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. ==Vehicle description== The Proton-M launch vehicle consists of 3 stages; all of them powered by liquid fueled engines using dinitrogen tetroxide and unsymmetrical dimethylhydrazine (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-2010, and 1 RD-0214 which is a 4 nozzle vernier engine used for thrust vector control. The nozzles of the RD-2014 can turn up to 45°; they are placed around (with some separation), and moderately above the nozzle of the RD-2013. 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 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. 抄文引用元・出典: フリー百科事典『 ウィキペディア（Wikipedia）』 ■ウィキペディアで「Proton-M」の詳細全文を読む スポンサード リンク
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