|
KTDU-80
The KTDU-80 (Russian: ) is the latest of a family of integrated propulsion system that KB KhIMMASH has implemented for the Soyuz since the Soyuz-T. It integrates main propulsion, RCS and attitude control in a single system pressure fed from a common dual string redundant pressurized propellant system. The common propellant is UDMH and 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 (the SKD), an RCS (the DPO-B) and an attitude control system (the DPO-M). All the propulsion elements are pressure fed rocket engines burning UDMH and N2O4 with a ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
11D428
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 manned 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 develope ... [...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 manned 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 develope ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
11D428A-16
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 manned 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 develope ... [...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 **MD5 ... [...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 **С5.86.1000-0 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. **S5.20 ... [...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). The Soyuz succeeded the Voskhod spacecraft and was originally built as part of the Soviet crewed lunar programs. It is launched on a Soyuz rocket from the Baikonur Cosmodrome in Kazakhstan. Between the 2011 retirement of the Space Shuttle and the 2020 demo flight of SpaceX Crew Dragon, the Soyuz served as the only means to ferry crew to or from the International Space Station, for which it remains heavily used. Although China did launch crewed Shenzhou flights during this time, none of them docked with the ISS. History The first Soyuz flight was uncrewed and started on 28 November 1966. The first Soyuz mission with a crew, Soyuz 1, launched on 23 April 1967 but ended with a crash due to a parachute failure, killing cosmonaut Vladimir Komarov. The following flight was uncrew ... [...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 viscous than 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 a propellant in rocketry. Hydrogen peroxide is a reactive oxygen species and the simplest peroxide, a compound having an oxygen–oxygen single bond. It decomposes slowly when exposed to light, and rapidly in the presence of organic or reactive compounds. It is typically stored with a stabilizer in a weakly acidic solution in a dark bottle to block light. Hydrogen peroxide is found in biological systems including the human body. Enzymes that use or decompose hydrogen peroxide are classified as peroxidases. Properties The boiling poi ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Catalysis
Catalysis () is the process of increasing the rate of a chemical reaction by adding a substance known as a catalyst (). Catalysts are not consumed in 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. Catalysis may be classified as either homogeneous, whose components are dispersed in the same phase (usually gaseous or liquid) as the reactant, or heterogeneous, whose components are not in the same phase. Enzymes and other biocatalysts are often considered as a third category. Catalysis is ubiquitous in chemical industry of all kinds. Estimates are that 90% of all commercially produced chemical products involve catalysts at some s ... [...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. Chemical-reaction monopropellant rockets For monopropellant rockets that depend on a chemical reaction, the power for the propulsive reaction and resultant thrust is provided by the chemical itself. That is, the energy needed to propel the spacecraft is contained within the chemical bonds of the chemical molecules involved in the reaction. The most commonly used monopropellant is hydrazine (N2H4), a chemical which is 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) or W.C.Heraeus H-KC 12 GA (previously made by Kali Chemie). There is no igniter with hydrazine. Aerojet S-405 is a spontaneous catalyst, that is, hydrazine decomposes on contact with the catalyst. The decomposition is highly exothermic and produce ... [...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 Russian rocket engineer. 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 (Замкнутая схема) was first proposed by Alexey Isaev in 194 ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Gas-generator Cycle
The gas-generator cycle is a power cycle of a pumped liquid bipropellant rocket engine. Part of the unburned propellant is burned in a gas generator (or preburner) 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 termed open cycle. Usage Gas-generator combustion engines include the following: * Vulcain, HM7B *Merlin *RS-68 *RS-27A *J-2X * F-1 *RD-107 * CE-20 * Rocket launch systems that use gas-generator combustion engines: *Ariane 5 *Falcon 9, Falcon Heavy *Delta IV *Saturn V *Soyuz * Geosynchronous Satellite Launch Vehicle III *Long March 3B, Long March 2F *Rocket Lab Neutron *Miura 5 See also * Combustion tap-off cycle * Expander cycle * Pressure-fed engine * 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, producin ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Reaction Control System
A reaction control system (RCS) is a spacecraft system that uses thrusters to provide attitude control and translation. Alternatively, reaction wheels are used for attitude control. Use of diverted engine thrust to provide stable attitude control of a short-or-vertical takeoff and landing aircraft below conventional winged flight speeds, such as with the 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 (roll, pitch, and yaw). Reaction control systems often use combinations of large and small ( vernier) thrusters, to allow different levels of response. Uses Spacecraft reaction control systems are used for: * attitude control during different stages of a mission; * station keeping in orbit; * close maneuvering during docking procedures; * control o ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
