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KTDU-80
The KTDU-80 (Russian language, Russian: ) is the latest of a family of integrated propulsion system that KB KhIMMASH has implemented for the Soyuz (spacecraft), Soyuz since the Soyuz-T. It integrates main propulsion, Reaction control system, RCS and Spacecraft attitude control, attitude control in a single system Pressure-fed engine, pressure fed from a common dual string redundant pressurized propellant system. The common propellant is Unsymmetrical dimethylhydrazine, UDMH and Dinitrogen tetroxide, N2O4 and the main propulsion unit is the S5.80 main engine. It generates of thrust with a chamber pressure of and a nozzle expansion of 153.8 that enables it to achieve a specific impulse of . It is rated for 30 starts with a total firing time of 890 seconds. The integrated system without the pressurization or tanks weighs ; it is long with a diameter of . Description The KTDU-80 system integrates a dual string redundant propellant and pressurization system, a main propulsion system ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
11D428
The 11D428A-16 (manufacturer's name RDMT-135M) is a Liquid-propellant rocket, liquid Pressure-fed engine, pressure-fed rocket engine burning Dinitrogen tetroxide, N2O4/Unsymmetrical dimethylhydrazine, UDMH with an Rocket propellant#Mixture ratio, O/F of 1.85. It is used for crew-rated spacecraft propulsion applications. It is currently used in the KTDU-80 spacecraft propulsion module. The previous version, the 11D428A (manufacturer's name RDMT-135) is still used as the reaction control system thrusters of the Zvezda (ISS module), Zvezda International Space Station, ISS module. The 11D428A-16 generates of thrust with a chamber pressure of and achieves a specific impulse of . It is rated for 500,000 starts with a certified ignition time of 0.03 seconds to 2000 seconds. Each unit weights . Versions This engine has been used with certain variations in the Human spaceflight, crewed Russian space program since the Salyut 6 in Soviet space program, Soviet times. The three main versions ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
11D428A
The 11D428A-16 (manufacturer's name RDMT-135M) is a liquid pressure-fed rocket engine burning N2O4/UDMH with an O/F of 1.85. It is used for crew-rated spacecraft propulsion applications. It is currently used in the KTDU-80 spacecraft propulsion module. The previous version, the 11D428A (manufacturer's name RDMT-135) is still used as the reaction control system thrusters of the Zvezda ISS module. The 11D428A-16 generates of thrust with a chamber pressure of and achieves a specific impulse of . It is rated for 500,000 starts with a certified ignition time of 0.03 seconds to 2000 seconds. Each unit weights . Versions This engine has been used with certain variations in the crewed Russian space program since the Salyut 6 in Soviet times. The three main versions are: * 11D428: Delivered in 1970 for use in Salyut 1. * 11D428M: Version developed for the Yantar-2K platform. It reached space on the first launch, Kosmos 697 on August 6, 1974. * 11D428A (AKA RDMT-135): Version dev ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Federal State Unitary Enterprise Research And Development Institute Of Mechanical Engineering
FSUE Research and Development Institute of Mechanical Engineering ( Russian: ), also known as NIIMash, is a Russian rocket engine design and manufacturing company specialized in small thrusters. It is located in the city of Nizhnyaya Salda, Sverdlovsk Oblast. It started as the B-175 factory of the NII-1 research institute, where Mikhail G. Mironov directed the development of liquid rocket engines research and testing. Products NIIMash has an extensive experience in design of testing stands, measurement and control as well as certifications. They also have a line of custom built air separation plants. They also have extensive experience in rotational forming of metals. The list of space rated products is extensive and is the following: Current propulsion products Engines in current production: *Propulsion **Experimental Reactive Control System Module **KDU 11D414NS ** Fobos-Grunt Sample Return Spacecraft Propulsion System **Fobos-Grunt Spacecraft Thruster Modules *Thrusters ** ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
KB KhIMMASH
The A.M. Isayev Chemical Engineering Design Bureau ( Russian: ), also known as KB KhimMash or just KBKhM, is a Russian rocket engine design and manufacturing company. It is located in the city of Korolyov. It started as the OKB-2 division of the NII-88 research institute, where A.Isaev directed the development of liquid rocket engines for ballistic missile submarines. Products Current engines Engines in current production: *Monopropellant Thrusters **DOT-5 **DOT-25 **MLC-10 **MLC-50 *Bipropellant Thrusters ** S5.142 (DST-25) **DST-50 **DST-100 **DST-100A **DST-200 **DST-200A **DMT-6 **DMT-500 **DMT-600 **DMT-1000 **DMT-2200 *Main propulsion ** S5.80 ** S5.92 ** S5.98 ** KVD-1 *Propulsion Modules **KTDU-80 *Experimental Engines **S5.86.1000-0 Former engines Engines that are no longer produced. *Monopropellant Thrusters **S5.70: Used on Phobos 1 spacecraft. **S5.70: Used on Phobos 1 spacecraft. *Bipropellant Thrusters **S5.144: Used on the control module 17D61 of the Ikar. **S5 ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Soyuz (spacecraft)
Soyuz () is a series of spacecraft which has been in service since the 1960s, having made more than 140 flights. It was designed for the Soviet space program by the Korolev Design Bureau (now Energia (corporation), Energia). The Soyuz succeeded the Voskhod spacecraft and was originally built as part of the Soviet crewed lunar programs. It is launched atop the similarly named Soyuz (rocket family), Soyuz rocket from the Baikonur Cosmodrome in Kazakhstan. Following the Soviet Union's dissolution, Roscosmos, the Russian space agency, continued to develop and utilize the Soyuz. Between the Space Shuttle retirement, Space Shuttle's 2011 retirement and the SpaceX Crew Dragon's 2020 debut, Soyuz was the sole means of crewed transportation to and from the International Space Station, a role it continues to fulfill. The Soyuz design has also influenced other spacecraft, including China's Shenzhou (spacecraft), Shenzhou and Russia's Progress (spacecraft), Progress cargo vehicle. The Soyu ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Hydrogen Peroxide
Hydrogen peroxide is a chemical compound with the formula . In its pure form, it is a very pale blue liquid that is slightly more viscosity, viscous than Properties of water, water. It is used as an oxidizer, bleaching agent, and antiseptic, usually as a dilute solution (3%–6% by weight) in water for consumer use and in higher concentrations for industrial use. Concentrated hydrogen peroxide, or "high-test peroxide", decomposes explosively when heated and has been used as both a monopropellant and an oxidizer in rocketry. Hydrogen peroxide is a reactive oxygen species and the simplest peroxide, a compound having an oxygen–oxygen single bond. It decomposes slowly into water and elemental oxygen when exposed to light, and rapidly in the presence of organic or reactive compounds. It is typically stored with a Stabilizer (chemistry), stabilizer in a weakly acidic solution in an opaque bottle. Hydrogen peroxide is found in biological systems including the human body. Enzymes that u ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Catalysis
Catalysis () is the increase in rate of a chemical reaction due to an added substance known as a catalyst (). Catalysts are not consumed by the reaction and remain unchanged after it. If the reaction is rapid and the catalyst recycles quickly, very small amounts of catalyst often suffice; mixing, surface area, and temperature are important factors in reaction rate. Catalysts generally react with one or more reactants to form intermediates that subsequently give the final reaction product, in the process of regenerating the catalyst. The rate increase occurs because the catalyst allows the reaction to occur by an alternative mechanism which may be much faster than the noncatalyzed mechanism. However the noncatalyzed mechanism does remain possible, so that the total rate (catalyzed plus noncatalyzed) can only increase in the presence of the catalyst and never decrease. Catalysis may be classified as either homogeneous, whose components are dispersed in the same phase (usual ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Monopropellant Rocket
A monopropellant rocket (or "monochemical rocket") is a rocket that uses a single chemical as its propellant. Monopropellant rockets are commonly used as small attitude and trajectory control rockets in satellites, rocket upper stages, crewed spacecraft, and spaceplanes. Chemical-reaction based monopropellant rockets The simplest monopropellant rockets depend on the chemical decomposition of a storable propellant after passing it over a catalyst bed. The power for the thruster comes from the high pressure gas created during the decomposition reaction that allows a Rocket engine nozzle, rocket nozzle to speed up the gas to create thrust. The most commonly used monopropellant is hydrazine (), a compound unstable in the presence of a Catalysis, catalyst and which is also a strong reducing agent. The most common catalyst is granular alumina (aluminum oxide, ) coated with iridium. These coated granules are usually under the commercial labels Aerojet S-405 (previously made by Shell plc, ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Aleksei Mihailovich Isaev
Aleksei Mikhailovich Isaev (also Isayev; Russian: Алексе́й Миха́йлович Иса́ев; October 24, 1908, in Saint Petersburg – June 10, 1971, in Moscow) was a Soviet engineer in the Soviet space program, working on rocket combustion and propellant. Aleksei Isaev began work under Leonid Dushkin during World War II, on an experimental rocket-powered interceptor plane, the BI-1. In 1944 he formed his own design bureau to engineer liquid-propellant engines. After abandoning the heavy, complex and undercooled German engine designs, Russia's principal engine designer Valentin Glushko turned to Isaev's innovations: thin-walled copper combustion chambers backed by steel support, anti-oscillation baffle to prevent chugging, and the flat injector plate with mixing-swirling injectors. The latter was an enormous simplification of the "plumbing nightmare" of the V-2 engine, because it avoided the need for separate fuel lines to each sprayer. Staged combustion (� ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Gas-generator Cycle
The gas-generator cycle, also referred to as the GG cycle or colloquially as an open cycle, is one of the most commonly used power cycles in bipropellant liquid rocket engines. Propellant is burned in a gas generator (analogous to, but distinct from, a preburner in a staged combustion cycle) and the resulting hot gas is used to power the propellant pumps before being exhausted overboard and lost. Because of this loss, this type of engine is considered an open cycle (note other open cycles exist, e.g. the tap-off bleed cycle). The gas generator cycle exhaust products pass over the turbine's rotor(s) first. Then they are expelled overboard. They can be expelled directly from the turbine, or are sometimes expelled into the nozzle (downstream from the throat) for both a small gain in efficiency, and can serve as film cooling. An advantage of this cycle is the high pressure drop available to the turbine (GG chamber pressure down to ambient) for extracting work from the drive gas; at ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Reaction Control System
A reaction control system (RCS) is a spacecraft system that uses Thrusters (spacecraft), thrusters to provide Spacecraft attitude control, attitude control and translation (physics), translation. Alternatively, reaction wheels can be used for attitude control, rather than RCS. Use of diverted engine thrust to provide stable attitude control of a V/STOL, short-or-vertical takeoff and landing aircraft below conventional winged flight speeds, such as with the Hawker Siddeley Harrier#Controls and handling, Harrier "jump jet", may also be referred to as a reaction control system. Reaction control systems are capable of providing small amounts of thrust in any desired direction or combination of directions. An RCS is also capable of providing torque to allow control of rotation (aircraft principal axes, roll, pitch, and yaw). Reaction control systems often use combinations of large and small (vernier thruster, vernier) thrusters, to allow different levels of response. Uses Spacecr ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
