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UR-500
Proton (Russian: Протон) (formal designation: UR-500) is an expendable launch system used for both commercial and Russian government space launches. The first Proton rocket was launched in 1965. Modern versions of the launch system are still in use as of 2022, making it one of the most successful heavy boosters in the history of spaceflight. The components of all Protons are manufactured at the Khrunichev State Research and Production Space Center factory in Moscow and Chemical Automatics Design Bureau in Voronezh, then transported to the Baikonur Cosmodrome, where they are assembled at Site 91 to form the launch vehicle. Following payload integration, the rocket is then brought to the launch pad horizontally by rail, and raised into vertical position for launch. As with many Soviet rockets, the names of recurring payloads became associated with the launch vehicle itself. The moniker "Proton" originates from a series of similarly named scientific satellites, which were amon ... [...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-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-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] |
Universal Rocket
The Universal Rocket or ''UR'' family of missiles and carrier rockets is a Russian, previously Soviet rocket family. Intended to allow the same technology to be used in all Soviet rockets, the UR is produced by the Khrunichev State Research and Production Space Center. Several variants were originally planned, of which only three flew, and only two of which entered service. In addition, the cancelled UR-500 ICBM formed the basis for the Proton carrier rocket. UR-100 The UR-100 and its variants (e.g. UR-100N) were the standard small ICBM of the Soviet Union during the Cold War. Only the UR-100N (NATO reporting designation: SS-19 Stiletto) remains in active duty, with 20–30 missiles operational. The Strela and Rokot carrier rockets are based on the UR-100N. A number of UR-100Ns have been earmarked for use as launch vehicles for the Avangard maneuverable reentry vehicle. UR-200 The UR-200 was intended to be a larger ICBM that could also be used as a carrier rocket. Nine test fl ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Khrunichev State Research And Production Space Center
The Khrunichev State Research and Production Space Center (''Государственный космический научно-производственный центр (ГКНПЦ) имени М. В. Хру́ничева'' in Russian) is a Moscow-based manufacturer of spacecraft and space-launch systems, including the Proton and Rokot rockets, and the Russian modules of Mir and the International Space Station. The company's history dates back to 1916, when an automobile factory was established at Fili, western suburb of Moscow. It soon switched production to airplanes and during World War II produced Ilyushin Il-4 and Tupolev Tu-2 bombers. A design bureau, OKB-23, was added to the company in 1951. In 1959, the company started developing intercontinental ballistic missiles, and later spacecraft and space launch vehicles. The company designed and produced all Soviet space stations, including Mir. OKB-23, renamed to ''Salyut Design Bureau'', became an independent company ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Baikonur Cosmodrome Site 81
Site 81 at the Baikonur Cosmodrome is a launch site used, along with Site 200, by Proton rockets. It consists of two launch pads, areas 23 and 24. Area 24 is used for Proton-K and Proton-M launches, while Area 23 is inactive. Several planetary probes have been launched from Site 81. Area 23 was used to launch Mars 3, Mars 4, Mars 6 and Venera 11, whilst Area 24 was used by Mars 2, Mars 5, Mars 7, Venera 9, Venera 10 and Venera 12. Several Luna programme, Luna probes were also launched from both areas. The Zarya (ISS module), Zarya and Zvezda (ISS module), Zvezda modules of the International Space Station, as well as Salyut 2, Salyut 3, 3 and Salyut 5, 5, and the Spektr and Priroda modules of Mir, were launched from Area 23. Area 24 was used to launch Salyut 1, Salyut 4, 4 and Salyut 6, 6. On 2 July 2013, a Proton-M 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 b ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
ViaSat-1
ViaSat-1 is a high throughput communications satellite owned by Viasat Inc. and Telesat Canada. Launched October 19, 2011 aboard a Proton rocket, it held the Guinness record for the world's highest capacity communications satellite with a total capacity in excess of 140 Gbit/s, more than all the satellites covering North America combined, at the time of its launch. ViaSat-1 is capable of two-way communications with small dish antennas at higher speeds and a lower cost-per-bit than any satellite before. The satellite is positioned at 115.1 degrees West longitude geostationary orbit point, with 72 Ka-band spot beams; 63 over the U.S. (Eastern and Western states, Alaska and Hawaii), and nine over Canada. The Canadian beams are owned by satellite operator Telesat and are used for the Xplornet broadband service to consumers in rural Canada. The US beams provide fast Internet access called Exede, Viasat's satellite Internet service. ViaSat-1 is part of a new satellite system archit ... [...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] |
UDMH
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] |
RD-275
The RD-253 ( russian: italic=yes, Раке́тный дви́гатель 253 , ''Rocket Engine 253'') and its later variants, the RD-275 and RD-275M, are liquid-propellant rocket engines developed in the Soviet Union by Energomash. The engines are used on the first stage of the Proton launch vehicle and use an oxidizer-rich staged combustion cycle to power the turbopumps. The engine burns UDMH/ N2O4, which are highly toxic but hypergolic and storable at room temperature, simplifying the engine's design. History Development of the RD-253 started in 1961. Preliminary investigations and development of the engine as well as its further production was performed under the guidance of Valentin Glushko and finished in 1963. The RD-253 uses a staged combustion cycle for oxidizer-rich generator gas. It was used for the first time in July 1965 when six engines powered the first stage of the rocket. Development and production of RD-253 was a qualitative leap forward for rocketry of that ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
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