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RD-193
The RD-193 is a high performance single-combustion chamber rocket engine, developed in Russia from 2011 to 2013. It is derived from the RD-170 originally used in the Energia launcher. The RD-193 is fueled by a kerosene / LOX mixture and uses an oxygen-rich staged combustion cycle. RD-193 was proposed as a replacement for the NK-33, which is being used in the Soyuz-2-1v vehicle. Design The engine is a simplified version of the RD-191, omitting the swing assembly chamber and its related structural elements, thus reducing size and weight (300 kg) and lowering cost. See also *Comparison of orbital rocket engines This page is an incomplete list of orbital rocket engine data and specifications. Current, Upcoming, and In-Development rocket engines Retired and canceled rocket engines See also * Comparison of orbital launch systems * Comparison of o ... References External links {{Russian and Soviet military designation sequences Rocket engines of Russia Ro ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Soyuz-2-1v
The Soyuz-2.1v (russian: Союз 2.1в, ''Union 2.1v''), GRAU index 14A15, known earlier in development as the Soyuz-1 (russian: Союз 1, ''Union 1''), is a Russian expendable launch vehicle. It was derived from the Soyuz-2.1b, and is a member of the R-7 family of rockets. It is built by TsSKB Progress, at Samara in Russia. Launches are conducted from existing facilities at the Plesetsk Cosmodrome in Northwest Russia, with pads also available at the Baikonur Cosmodrome in Kazakhstan, and new facilities at the Vostochny Cosmodrome in Eastern Russia. Vehicle The Soyuz-2.1v represents a major departure from earlier Soyuz rockets. Unlike the Soyuz-2.1b upon which it is based, it does away with the four boosters used on all other R-7 vehicles. The first stage of the Soyuz-2.1v is a heavily modified derivative of the Soyuz-2 second stage, with a single-chamber NK-33 engine replacing the four-chamber RD-107 used on previous rockets along with structural modifications to the s ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
RD-170 (rocket Engine)
The RD-170 ( rus, РД-170, Ракетный Двигатель-170, Raketnyy Dvigatel-170) is the world's most powerful and heaviest liquid-fuel rocket engine. It was designed and produced in the Soviet Union by NPO Energomash for use with the Energia launch vehicle. The engine burns kerosene fuel and LOX oxidizer in four combustion chambers, all supplied by one single-shaft, single-turbine turbopump rated at in a staged combustion cycle. Shared turbopump Several Soviet and Russian rocket engines use the approach of clustering small combustion chambers around a single turbine and pump. During the early 1950s, many Soviet engine designers, including Valentin P. Glushko, faced problems of combustion instability while designing bigger thrust chambers. At that time, they solved the problem by using a cluster of smaller thrust chambers. Variants RD-170 The RD-170 engine featured four combustion chambers and was developed for use on the Energia launch vehicle – both the e ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
NK-33
The NK-33 and NK-43 are rocket engines designed and built in the late 1960s and early 1970s by the Kuznetsov Design Bureau. The NK designation is derived from the initials of chief designer Nikolay Kuznetsov. The NK-33 was among the most powerful LOX/RP-1 rocket engines when it was built, with a high specific impulse and low structural mass. They were intended for the ill-fated Soviet N1F moon rocket, which was an upgraded version of the N1. The NK-33A rocket engine is now used on the first stage of the Soyuz-2-1v launch vehicle. When the supply of the NK-33 engines are exhausted, Russia will supply the new RD-193 rocket engine. It used to be the first stage engines of the Antares 100 rocket series, although those engines are rebranded the AJ-26 and the newer Antares 200 and Antares 200+ rocket series uses the RD-181 for the first stage engines, which is a modified RD-191, but shares some properties like a single combustion chamber unlike the two combustion chambers used in the ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Comparison Of Orbital Rocket Engines
This page is an incomplete list of orbital rocket engine data and specifications. Current, Upcoming, and In-Development rocket engines Retired and canceled rocket engines See also * Comparison of orbital launch systems * Comparison of orbital launchers families * Comparison of crewed space vehicles * Comparison of space station cargo vehicles * Comparison of solid-fuelled orbital launch systems * List of space launch system designs * List of orbital launch systems This is a list of conventional orbital launch systems. This is composed of launch vehicles, and other conventional systems, used to place satellites into orbit. Argentina *ORBIT II – ''Retired'' * TRONADOR – ''Under Development'' Australia ... Notes References {{DEFAULTSORT:Orbital rocket engine comparison Spaceflight Technological comparisons Space lists Rocket engines ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Russia
Russia (, , ), or the Russian Federation, is a List of transcontinental countries, transcontinental country spanning Eastern Europe and North Asia, Northern Asia. It is the List of countries and dependencies by area, largest country in the world, with its internationally recognised territory covering , and encompassing one-eighth of Earth's inhabitable landmass. Russia extends across Time in Russia, eleven time zones and shares Borders of Russia, land boundaries with fourteen countries, more than List of countries and territories by land borders, any other country but China. It is the List of countries and dependencies by population, world's ninth-most populous country and List of European countries by population, Europe's most populous country, with a population of 146 million people. The country's capital and List of cities and towns in Russia by population, largest city is Moscow, the List of European cities by population within city limits, largest city entirely within E ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
NPO Energomash
NPO Energomash “V. P. Glushko” is a major Russian rocket engine manufacturer. The company primarily develops and produces liquid propellant rocket engines. Energomash originates from the Soviet design bureau OKB-456, which was founded in 1946. NPO Energomash acquired its current name on May 15, 1991, in honor of its former chief designer Valentin Glushko. Energomash is noted for its long history of large scale LOX/Kerosene engine development. Notable examples are the RD-107/ RD-108 engines used on the R-7, Molniya and Soyuz rocket families, and the RD-170, RD-171 and RD-180 engines used on the Energia, Zenit and Atlas V launch vehicles. , the company remained largely owned by the federal government of Russia, but RSC Energia owned approximately 14% of the total shares. , NPO Energomash employed approximately 5500 workers at its headquarters in Khimki, Moscow and its satellite facilities in Samara, Perm, and St. Petersburg. On 4 August 2016, the company announced ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Staged Combustion Cycle (rocket)
The staged combustion cycle (sometimes known as topping cycle, preburner cycle, or closed cycle) is a Liquid-propellant rocket#Engine cycles, power cycle of a bipropellant rocket Rocket engine, engine. In the staged combustion cycle, propellant flows through multiple Rocket engine#Combustion chamber, combustion chambers, and is thus combustion, combusted in stages. The main advantage relative to other rocket engine power cycles is high fuel efficiency, measured through specific impulse, while its main disadvantage is reliability engineering, engineering complexity. Typically, propellant flows through two kinds of combustion chambers; the first called preburner and the second called main combustion chamber. In the preburner, a small portion of propellant, usually fuel-rich, is partly combusted, and the increasing volume flow is used to drive the turbopumps that feed the engine with propellant. The gas is then injected into the main combustion chamber and combusted completely with ... [...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] |
Combustion Chamber
A combustion chamber is part of an internal combustion engine in which the fuel/air mix is burned. For steam engines, the term has also been used for an extension of the firebox which is used to allow a more complete combustion process. Internal combustion engines In an internal combustion engine, the pressure caused by the burning air/fuel mixture applies direct force to part of the engine (e.g. for a piston engine, the force is applied to the top of the piston), which converts the gas pressure into mechanical energy (often in the form of a rotating output shaft). This contrasts an external combustion engine, where the combustion takes place in a separate part of the engine to where the gas pressure is converted into mechanical energy. Spark-ignition engines In spark ignition engines, such as petrol (gasoline) engines, the combustion chamber is usually located in the cylinder head. The engines are often designed such that the bottom of combustion chamber is roughly in li ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
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 accordance with Newton's third law. Most rocket engines use the combustion of reactive chemicals to supply the necessary energy, but non-combusting forms such as cold gas thrusters and nuclear thermal rockets also exist. Vehicles propelled by rocket engines are commonly called rockets. Rocket vehicles carry their own oxidiser, unlike most combustion engines, so rocket engines can be used in a vacuum to propel spacecraft and ballistic missiles. Compared to other types of jet engine, rocket engines are the lightest and have the highest thrust, but are the least propellant-efficient (they have the lowest specific impulse). The ideal exhaust is hydrogen, the lightest of all elements, but chemical rockets produce a mix of heavier species, reducing the e ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Energia (rocket)
Energia (russian: Энергия, Energiya, Energy; GRAU 11K25) was a 1980s super-heavy lift launch vehicle. It was designed by NPO Energia of the Soviet Union as part of the Buran programme, Buran program for a variety of payloads including the Buran (spacecraft), Buran spacecraft. Control system main developer enterprise was the Khartron NPO "Electropribor". The Energia used four strap-on boosters each powered by a four-chamber RD-170 engine burning kerosene/Liquid oxygen, LOX, and a central core stage with four single-chamber RD-0120 (11D122) engines fueled by liquid hydrogen/LOX. The launch vehicle had two functionally different operational variants: Energia-Polyus, the initial test configuration, in which the Polyus (spacecraft), Polyus system was used as a final stage intended to put the payload into orbit, and Energia-Buran, in which the Buran programme, ''Buran'' orbiter was the payload and the source of the orbit insertion impulse. The launch vehicle had the capacity to ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
