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Proton Medium
The Proton-M, (Протон-М) GRAU index 8K82M or , is an expendable 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. Proton flew its most recent mission on 13 December 2021, launching two Ekspress communication satellites into geostationary orbit. As of August 2020, a number of Roscosmos and other Russian government missions remain on Proton launch manifest. Vehicle description The Proton-M launch vehicle consists of three stages; all of them powered by liquid rocket engines using the hypergolic propellant combination of dinitrogen tetroxide as the oxidizer, and unsymmetrical dimethylhydrazine for fuel. The first stage is unique in that it consists of a central cylindrical oxidizer ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Baikonur Cosmodrome
The Baikonur Cosmodrome ( kk, Байқоңыр ғарыш айлағы, translit=Baiqoñyr ğaryş ailağy, ; russian: Космодром Байконур, translit=Kosmodrom Baykonur, ) is a spaceport in an area of southern Kazakhstan leased to Russia. The Cosmodrome is the world's first spaceport for orbital and human launches and the largest (in area) operational Spaceport, space launch facility. All crewed Russian spaceflights are launched from Baikonur. The spaceport is in the Kazakh Steppe, desert steppe of Baikonur, about east of the Aral Sea and north of the river Syr Darya. It is near the Tyuratam railway station and is about above sea level. The spaceport is currently leased by the Government of Kazakhstan, Kazakh Government to the Russian Federation until 2050 and is managed jointly by the Roscosmos State Corporation, Roscosmos and the Russian Aerospace Forces. The shape of the area leased is an ellipse, measuring east–west by north–south, with the cosmodrome at ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
GLONASS
GLONASS (russian: ГЛОНАСС, label=none, ; rus, links=no, Глобальная навигационная спутниковая система, r=Global'naya Navigatsionnaya Sputnikovaya Sistema, t=Global Navigation Satellite System) is a Russian satellite navigation system operating as part of a radionavigation-satellite service. It provides an alternative to Global Positioning System (GPS) and is the second navigational system in operation with global coverage and of comparable precision. Satellite navigation devices supporting both GPS and GLONASS have more satellites available, meaning positions can be fixed more quickly and accurately, especially in built-up areas where buildings may obscure the view to some satellites. GLONASS supplementation of GPS systems also improves positioning in high latitudes (north or south). Development of GLONASS began in the Soviet Union in 1976. Beginning on 12 October 1982, numerous rocket launches added satellites to the system, unti ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Liquid Oxygen
Liquid oxygen—abbreviated LOx, LOX or Lox in the aerospace, submarine and gas industries—is the liquid form of molecular oxygen. It was used as the oxidizer in the first liquid-fueled rocket invented in 1926 by Robert H. Goddard, an application which has continued to the present. Physical properties Liquid oxygen has a pale blue color and is strongly paramagnetic: it can be suspended between the poles of a powerful horseshoe magnet. Liquid oxygen has a density of , slightly denser than liquid water, and is cryogenic with a freezing point of and a boiling point of at . Liquid oxygen has an expansion ratio of 1:861 under and , and because of this, it is used in some commercial and military aircraft as a transportable source of breathing oxygen. Because of its cryogenic nature, liquid oxygen can cause the materials it touches to become extremely brittle. Liquid oxygen is also a very powerful oxidizing agent: organic materials will burn rapidly and energetically in liquid o ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
RP-1
RP-1 (alternatively, Rocket Propellant-1 or Refined Petroleum-1) is a highly refined form of kerosene outwardly similar to jet fuel, used as rocket fuel. RP-1 provides a lower specific impulse than liquid hydrogen (LH2), but is cheaper, is stable at room temperature, and presents a lower explosion hazard. RP-1 is far denser than LH2, giving it a higher energy density (though its specific energy is lower). RP-1 also has a fraction of the toxicity and carcinogenic hazards of hydrazine, another room-temperature liquid fuel. Usage and history RP-1 is a fuel in the first-stage boosters of the Electron, Soyuz, Zenit, Delta I-III, Atlas, Falcon, Antares, and Tronador II rockets. It also powered the first stages of the Energia, Titan I, Saturn I and IB, and Saturn V. The Indian Space Research Organization (ISRO) is also developing an RP-1 fueled engine for its future rockets. Development During and immediately after World War II, alcohols (primarily ethanol, occasionally metha ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
RD-58M
The RD-58 (manufacturer designation 11D58) is a rocket engine, developed in the 1960s by OKB-1, now RKK Energia. The project was managed by Mikhail Melnikov, and it was based on the previous S1.5400 which was the first staged combustion engine in the world. The engine was initially created to power the Block D stage of the Soviet Union's abortive N-1 rocket. Derivatives of this stage are now used as upper stages on some Proton and Zenit rockets. An alternative version of the RD-58 chamber, featuring a shorter nozzle, was used as the N-1's roll-control engine. The RD-58 uses LOX as the oxidizer and RG-1 as fuel in an oxidizer rich staged combustion cycle. It features a single gimbaled chamber, radial centrifugal pumps with auxiliary booster pumps, and an oxygen-rich preburner. Recent modifications include a lightweight carbon-composite nozzle extender developed by NPO Iskra. The Buran spacecraft used two of an evolution of the RD-58M, called 17D12, as its main orbital correc ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Blok D
Blok D (russian: Блок Д meaning Block D) is an upper stage used on Soviet and later Russian expendable launch systems, including the N1, Proton-K and Zenit. The stage (and its derivatives) has been included in more than 320 launched rockets . By 2002 its modification Blok DM had a 97% success rate in 218 flights since 1974, and 43 successful missions in 1997–2002. The stage was developed in 1960s as the fifth stage (' Д' is the fifth letter in the Cyrillic alphabet) for the Soviet Moonshot N1 rocket. The stage first flew in March 1967 while testing Zond of the moonshot program system. During manned lunar flight Blok D would be used for mid-course corrections on the flight to the Moon, then to place the lunar orbiter and lander into a lunar orbit, and decelerate moon-lander out onto its landing trajectory. Blok D was also included as fourth stage of Proton-K and as such flew on unmanned Soviet missions to Moon, Mars (Mars 3) and Venus. It was used in the Proton-K co ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Briz (rocket Stage)
The Briz-K, Briz-KM and Briz-M (russian: Бриз-К, КM and M meaning ''Breeze-K, KM and M'') are Russian liquid-propellant rocket orbit insertion upper stages manufactured by Khrunichev State Research and Production Space Center and used on the Proton-M and Angara A5. The upper stages were also used on Rokot, one of Russia's smaller launchers, before its retirement in 2019. Characteristics Briz-K and Briz-KM Briz-K, GRAU index 14S12, is a single-piece structure with a conical tank compartment and the engine located in a recess in the fuel tank. Briz-KM (GRAU index 14S45) is an improved version of Briz-K. The Briz-K and Briz-KM were used as a third stage of the Rokot launch vehicles. Briz-M Briz-M, GRAU index 14S43, is designed for injecting large payloads into a low, medium-height or high geosynchronous orbit. Briz-M is a twin upper stage consisting of a core module (using Briz-KM as the baseline) and a jettisonable add-on toroidal tank surrounding the core. It is po ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
RD-0212
The RD-0210 ( GRAU Index: 8D411K) is also known as the RD-465. It and its twin, the RD-0211, are rocket engines burning N2O4 and UDMH in an oxidizer rich staged combustion cycle. They have single nozzle, possess TVC and are the latest evolution in the RD-0203/4 lineage. They are the engines used on the Proton second stage. The RD-0213 is a fixed nozzle variation that is used on the RD-0212 module of the Proton third stage. Development When Chelomey's OKB-52 started their UR-200 ICBM project, they requested S. A. Kosberg's OKB-154 to develop the propulsion. They decided to use the same basic block for both the first and second stage. But to achieve the required performance, Kosberg had to develop a staged combustion engine, a then extremely aggressive feat. Only M. V. Melnikov of OKB-1 had designed a staged combustion engine before, the S1.5400, and it used a different propellant mix with significantly less thrust. To simplify design and manufacture, the engine would b ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
RD-0211
The RD-0210 ( GRAU Index: 8D411K) is also known as the RD-465. It and its twin, the RD-0211, are rocket engines burning N2O4 and UDMH in an oxidizer rich staged combustion cycle. They have single nozzle, possess TVC and are the latest evolution in the RD-0203/4 lineage. They are the engines used on the Proton second stage. The RD-0213 is a fixed nozzle variation that is used on the RD-0212 module of the Proton third stage. Development When Chelomey's OKB-52 started their UR-200 ICBM project, they requested S. A. Kosberg's OKB-154 to develop the propulsion. They decided to use the same basic block for both the first and second stage. But to achieve the required performance, Kosberg had to develop a staged combustion engine, a then extremely aggressive feat. Only M. V. Melnikov of OKB-1 had designed a staged combustion engine before, the S1.5400, and it used a different propellant mix with significantly less thrust. To simplify design and manufacture, the engine would b ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
RD-0210
The RD-0210 ( GRAU Index: 8D411K) is also known as the RD-465. It and its twin, the RD-0211, are rocket engine A rocket engine uses stored rocket propellants as the reaction mass for forming a high-speed propulsive jet of fluid, usually high-temperature gas. Rocket engines are reaction engines, producing thrust by ejecting mass rearward, in accordanc ...s burning N2O4 and Unsymmetrical dimethylhydrazine, UDMH in an Staged combustion cycle (rocket), oxidizer rich staged combustion cycle. They have single nozzle, possess Thrust vectoring, TVC and are the latest evolution in the RD-0203, RD-0203/4 lineage. They are the engines used on the Proton (rocket family), Proton second stage. The RD-0213 is a fixed nozzle variation that is used on the RD-0212 module of the Proton (rocket family), Proton third stage. Development When Vladimir Chelomey, Chelomey's OKB-52 started their UR-200 ICBM project, they requested Semyon Kosberg, S. A. Kosberg's Chemical Automatics Design Burea ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Unsymmetrical Dimethylhydrazine
Unsymmetrical dimethylhydrazine (UDMH; 1,1-dimethylhydrazine, НДМГ or codenamed Geptil) is a chemical compound with the formula H2NN(CH3)2 that is used as a rocket propellant. It is a colorless liquid, with a sharp, fishy, ammonia-like smell typical for organic amines. Samples turn yellowish on exposure to air and absorb oxygen and carbon dioxide. It is miscible with water, ethanol, and kerosene. In concentration between 2.5% and 95% in air, its vapors are flammable. It is not sensitive to shock. Symmetrical dimethylhydrazine, 1,2-dimethylhydrazine is also known but is not as useful. Production UDMH is produced industrially by two routes. Based on the Olin Raschig process, one method involves reaction of monochloramine with dimethylamine giving 1,1-dimethylhydrazinium chloride: :(CH3)2NH + NH2Cl → (CH3)2NNH2 ⋅ HCl In the presence of suitable catalysts, acetylhydrazine can be N-dimethylated using formaldehyde and hydrogen to give the N,N-dimethyl-N'-acetylhydrazine, w ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Dinitrogen Tetroxide
Dinitrogen tetroxide, commonly referred to as nitrogen tetroxide (NTO), and occasionally (usually among ex-USSR/Russia rocket engineers) as amyl, is the chemical compound N2O4. It is a useful reagent in chemical synthesis. It forms an equilibrium mixture with nitrogen dioxide. Its molar mass is 92.011 g/mol. Dinitrogen tetroxide is a powerful oxidizer that is hypergolic (spontaneously reacts) upon contact with various forms of hydrazine, which has made the pair a common bipropellant for rockets. Structure and properties Dinitrogen tetroxide could be regarded as two nitro groups (-NO2) bonded together. It forms an equilibrium mixture with nitrogen dioxide. The molecule is planar with an N-N bond distance of 1.78Å and N-O distances of 1.19Å. The N-N distance corresponds to a weak bond, since it is significantly longer than the average N-N single bond length of 1.45Å. This exceptionally weak σ bond (amounting to overlapping of the ''sp''2 hybrid orbitals of the two NO2 units) ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
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