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NK-43
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] |
Kuznetsov Design Bureau
The Kuznetsov Design Bureau (russian: СНТК им. Н. Д. Кузнецова, also known as OKB-276) was a Russian design bureau for aircraft engines, administrated in Soviet times by Nikolai Dmitriyevich Kuznetsov. It was also known as (G)NPO Trud (or NPO Kuznetsov) and Kuybyshev Engine Design Bureau (KKBM). NPO Trud was replaced in 1994 by a Joint Stock Company (JSC), Kuznetsov R & E C. By the early 2000s the lack of funding caused by the poor economic situation in Russia had brought Kuznetsov on the verge of bankruptcy. In 2009 the Russian government decided to consolidate a number of engine-making companies in the Samara region under a new legal entity. This was named JSC Kuznetsov, after the design bureau. Products The Kuznetzov Bureau first became notable for producing the monstrous Kuznetsov NK-12 turboprop engine that powered the Tupolev Tu-95 bomber beginning in 1952 as a development of the Junkers 0022 engine. The new engine eventually generated about 15,000 horse ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
JSC Kuznetsov
JSC Kuznetsov (russian: ПАО «Кузнецов») is one of the leading Russian producers of aircraft engines, liquid-propellant rocket engines as well as aeroderivative gas turbines and modular stations. The current joint-stock company was established through the consolidation of several Samara-based aerospace engine companies, including JSC N.D. Kuznetsov SNTK, JSC Samara Design Bureau of Machine Building and JSC NPO Povolzhskiy AviTI. History The company was established in 1912 as the Gnome Factory of Moscow, after the French aircraft engine company Gnome et Rhône which supplied the engine parts assembled by the plant. In 1925 it was renamed 'Frunze Factory No. 24', after Bolshevik leader Mikhail Frunze. The factory was evacuated to its current location in Samara in 1941. The Samara Frunze Engine-Building Production Association was one of the principal aerospace engine production complexes in Russia, with six plants and 25,000 employees in the early 1990s. It has produced ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
N1 (rocket)
The N1/L3 (from , "Carrier Rocket"; Cyrillic: Н1) was a super heavy-lift launch vehicle intended to deliver payloads beyond low Earth orbit. The N1 was the Soviet counterpart to the US Saturn V and was intended to enable crewed travel to the Moon and beyond, with studies beginning as early as 1959. Its first stage, Block A, remains the most powerful rocket stage ever flown. However, all four first stages flown failed mid-flight because a lack of static test firings meant that plumbing issues and other adverse characteristics with the large cluster of thirty engines and its complex fuel and oxidizer feeder system were not revealed earlier in development. The N1-L3 version was designed to compete with the United States Apollo program to land a person on the Moon, using a similar lunar orbit rendezvous method. The basic N1 launch vehicle had three stages, which were to carry the L3 lunar payload into low Earth orbit with two cosmonauts. The L3 contained one stage for trans-lun ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Nikolai Dmitriyevich Kuznetsov
Nikolai Dmitriyevich Kuznetsov was a Chief Designer of the Soviet Design Bureau OKB-276 which deals with the development, manufacture and distribution of equipment, especially aircraft engines, turbines and gearboxes. Biography Kuznetsov started his career as a professional coppersmith and he began working as a mechanic. In 1930 graduated from the school and enrolled at the "Moscow Aviation College" where he studied part-time and worked as a mechanic. In 1933, he joined the Air Technical School in the Motor Branch of "VVIA of Zhukovsky". There he studied under Prof. Nikolai Jegorowitsch Schukowski - then the head of the department for aircraft engines research, and Kuznetsov received a degree with honors in November 1938. The topic of his diploma there was on motors: four-carburettor, 28-cylinder with a 4-star air-cooled power of 1500 hp at 3400 rpm and at an altitude of 6000 meters with two-high-speed driven centrifugal blowers. In April 1939, Kuznetsov became a me ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Aerojet
Aerojet was an American rocket and missile propulsion manufacturer based primarily in Rancho Cordova, California, with divisions in Redmond, Washington, Orange and Gainesville in Virginia, and Camden, Arkansas. Aerojet was owned by GenCorp. In 2013, Aerojet was merged by GenCorp with the former Pratt & Whitney Rocketdyne to form Aerojet Rocketdyne. History Aerojet developed from a 1936 meeting hosted by Theodore von Kármán at his home. Joining von Kármán, who was at the time director of Guggenheim Aeronautical Laboratory at the California Institute of Technology, were a number of Caltech professors and students, including rocket scientist and astrophysicist Fritz Zwicky and explosives expert Jack Parsons, all of whom were interested in the topic of spaceflight. The group continued to occasionally meet, but its activities were limited to discussions rather than experimentation. Their first design was tested on August 16, 1941, consisting of a small cylindrical solid-fuel ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Simplified Diagram Of NK33 Rocket Engine , Jan 2021 (English Verson)
Simplification, Simplify, or Simplified may refer to: Mathematics Simplification is the process of replacing a mathematical expression by an equivalent one, that is simpler (usually shorter), for example * Simplification of algebraic expressions, in computer algebra * Simplification of boolean expressions i.e. logic optimization * Simplification by conjunction elimination in inference in logic yields a simpler, but generally non-equivalent formula * Simplification of fractions Science * Approximations simplify a more detailed or difficult to use process or model Linguistics * Simplification of Chinese characters * Simplified English (other) * Text simplification Music * Simplified (band), a 2002 rock band from Charlotte, North Carolina * ''Simplified'' (album), a 2005 album by Simply Red * "Simplify", a 2008 song by Sanguine * "Simplify", a 2018 song by Young the Giant from ''Mirror Master'' See also * Muntzing (simplification of electric circuits) * Reduction (math ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
RD-108
The RD-107 and its sibling, the RD-108, are a type of rocket engine initially used to launch R-7 Semyorka missiles. RD-107 engines were later used on space launch vehicles based on the R-7. , very similar RD-107A and RD-108A engines are used to launch the Soyuz-2.1a, and Soyuz-2.1b, which are in active service. Design The RD-107 was designed under the direction of Valentin Glushko at the Experimental Design Bureau (OKB-456) between 1954 and 1957. It uses liquid oxygen and kerosene as propellants operating in a gas generator cycle. As was typical by all the descendants of the V-2 rocket technology, the turbine is driven by steam generated by catalytic decomposition of H₂O₂. The steam generator uses solid ''F-30-P-G'' catalyst. These are based on a variable sized pellet covered in an aqueous solution of potassium permanganate and sodium. Each engine uses four fixed main combustion chambers. The RD-107 has an additional two vernier combustion chambers that can thrust vecto ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Liquid-propellant Rocket
A liquid-propellant rocket or liquid rocket utilizes a rocket engine that uses liquid rocket propellant, liquid propellants. Liquids are desirable because they have a reasonably high density and high Specific impulse, specific impulse (''I''sp). This allows the volume of the propellant tanks to be relatively low. It is also possible to use lightweight centrifugal turbopumps to pump the rocket propellant from the tanks into the combustion chamber, which means that the propellants can be kept under low pressure. This permits the use of low-mass propellant tanks that do not need to resist the high pressures needed to store significant amounts of gasses, resulting in a low mass ratio for the rocket. An inert gas stored in a tank at a high pressure is sometimes used instead of pumps in simpler small engines to force the propellants into the combustion chamber. These engines may have a higher mass ratio, but are usually more reliable, and are therefore used widely in satellites for orbit ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Staged Combustion Cycle
The staged combustion cycle (sometimes known as topping cycle, preburner cycle, or closed cycle) is a power cycle of a bipropellant rocket engine. In the staged combustion cycle, propellant flows through multiple combustion chambers, and is thus 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 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 the other propellant to produce thrust. Tradeoffs The main advantage is fuel efficiency due to all of the propellant flo ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
RD-170
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 eng ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
