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AJ-26
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 Nikolai Dmitriyevich Kuznetsov, 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 N1 (rocket), 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 (rocket), 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-191, RD-181 for the first stage engines, which is a modified RD-191, but shares some properties like a singl ... [...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] |
Antares (rocket)
Development The NASA COTS award was for and Orbital Sciences expected to invest an additional $150 million, split between $130 million for the booster and $20 million for the spacecraft. A Commercial Resupply Service contract of $1.9 billion for eight flights was awarded in 2008. As of April 2012, development costs were estimated at $472 million. In June 2008, it was announced that the Mid-Atlantic Regional Spaceport, formerly part of the Wallops Flight Facility, in Virginia, would be the primary launch site for the rocket. Launch pad 0A (LP-0A), previously used for the failed Conestoga rocket, would be modified to handle Antares. Wallops allows launches which reach the International Space Station's orbit as effectively as those from Cape Canaveral, Florida, while being less crowded. The first Antares flight launched a Cygnus mass simulator. On December 10, 2009, Alliant Techsystems Inc. (ATK) test-fired their Castor 30 motor for use on the second stage of the Antar ... [...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] |
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] |
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] |
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] |
NK-15
The NK-15 (GRAU index 11D51) was a rocket engine designed and built in the late 1960s by the Kuznetsov Design Bureau. The NK designation was derived from the initials of chief designer Nikolay Kuznetsov. The NK-15 was among the most powerful LOX/kerosene rocket engines when it was built, with a high specific impulse and low structural mass. It was intended for the ill-fated Soviet N-1 Moon rocket. History The engine equipped the N1 rocket - the first two launch attempts failed due to this engine. Its successor the NK-33 was to be used on the N1F, a new version of the N1, but the program was cancelled. Versions * NK-15V (GRAU index 11D52): Modified NK-15 optimized for vacuum operation, used on the N1 second stage. See also *Comparison of orbital rocket engines References NK-15 ''Encyclopedia Astronautica The ''Encyclopedia Astronautica'' is a reference web site on space travel. A comprehensive catalog of vehicles, technology, astronauts, and flights, it includes ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
RD-107
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] |
Thrust-to-weight Ratio
Thrust-to-weight ratio is a dimensionless ratio of thrust to weight of a rocket, jet engine, propeller engine, or a vehicle propelled by such an engine that is an indicator of the performance of the engine or vehicle. The instantaneous thrust-to-weight ratio of a vehicle varies continually during operation due to progressive consumption of fuel or propellant and in some cases a gravity gradient. The thrust-to-weight ratio based on initial thrust and weight is often published and used as a figure of merit for quantitative comparison of a vehicle's initial performance. Calculation The thrust-to-weight ratio is calculated by dividing the thrust (in SI units – in newtons) by the weight (in newtons) of the engine or vehicle. Note that the thrust can also be measured in pound-force (lbf), provided the weight is measured in pounds (lb). Division using these two values still gives the numerically correct (dimensionless) thrust-to-weight ratio. For valid comparison of the initial th ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Corrugated
The term corrugated, describing a series of parallel ridges and furrows, may refer to the following: Materials *Corrugated fiberboard, also called corrugated cardboard *Corrugated galvanised iron, a building material composed of sheets of cold-rolled hot-dip galvanised mild steel *Corrugated plastic, a wide range of extruded twinwall plastic-sheet products produced from high-impact polypropylene resin *Corrugated stainless steel tubing, tubing made of stainless steel with corrugation on the inside or outside Animals *Corrugated darter, a species of fish endemic to the eastern United States *Corrugated pipefish, a marine fish of the family Syngnathidae *Corrugated frog, a species of frog in the family Dicroglossidae *Corrugated water frog, a species of frog in the family Nyctibatrachidae *Corrugated nutmeg, a species of sea snail Other uses * Corrugaphone or whirly tube, an experimental musical instrument or toy * Corrugated road, a form of damage prone to develop in the surface ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Integrated Powerhead Demonstrator
The integrated powerhead demonstrator (IPD) was a U.S. Air Force project in the 1990s and early 2000s run by NASA and the Air Force Research Laboratory (AFRL) to develop a new rocket engine front-end ("powerhead", sometimes also termed a powerpack) that would utilize a full flow staged combustion cycle (FFSCC). The prime contractors were Rocketdyne and Aerojet. The long-term design goal was to apply the advantages of FFSCC to create a reusable engine with improved life, reliability and performance. The powerhead demonstrator project was to develop a demonstrator design of what could become the front-end for a future engine development project. No subsequent funding was made available by public policymakers, so no full engine design was ever completed. The turbines were also planned to feature hydrostatic bearings instead of the traditional ball bearings. More details can be seen at: https://apps.dtic.mil/sti/pdfs/ADA430218.pdf Videos: Integrated Powerhead Demonstration ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
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