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Aerojet LR91
The LR91 was an American liquid-fuel rocket, liquid-propellant rocket engine, which was used on the second stages of Titan (rocket family), Titan intercontinental ballistic missiles and Titan (rocket family), launch vehicles. While the original version - the LR91-3 - ran on RP-1/LOX (as did the companion LR87#Versions, LR87-3) on the HGM-25A Titan I, Titan I, the models that propelled the LGM-25C Titan II, Titan II and later were switched to Aerozine 50/nitrogen tetroxide, N2O4. This engine was vacuum optimized and ran the gas-generator cycle (rocket), gas-generator cycle. The thrust chamber used fuel for regenerative cooling (rocket), regenerative cooling, with separate ablation, ablative skirt. The LR87, which was used for the Titan first stage, was used as a template for the LR91. Early LR91 engines used on the Titan I burned RP-1 and liquid oxygen. Because liquid oxygen is cryogenic, it could not be stored in the missile for long periods of time, and had to be loaded before t ... [...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, Inc., 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 s ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Regenerative Cooling (rocket)
In rocket engine design, regenerative cooling is a configuration in which some or all of the propellant is passed through tubes, channels, or in a jacket around the combustion chamber or nozzle to cool the engine. This is effective because the propellants are often cryogenic. The heated propellant is then fed into a special gas-generator or injected directly into the main combustion chamber. History In 1857 Carl Wilhelm Siemens introduced the concept of regenerative cooling. On 10 May 1898, James Dewar used regenerative cooling to become the first to statically liquefy hydrogen. The concept of regenerative cooling was also mentioned in 1903 in an article by Konstantin Tsiolkovsky. Robert Goddard built the first regeneratively cooled engine in 1923, but rejected the scheme as too complex. A regeneratively cooled engine was built by the Italian researcher, Gaetano Arturo Crocco in 1930. The first Soviet engines to employ the technique were Fridrikh Tsander's OR-2 tested i ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Rocket Engines Using Kerosene Propellant
A rocket (from , and so named for its shape) is a vehicle that uses jet propulsion to accelerate without using any surrounding air. A rocket engine produces thrust by reaction to exhaust expelled at high speed. Rocket engines work entirely from propellant carried within the vehicle; therefore a rocket can fly in the vacuum of space. Rockets work more efficiently in a vacuum and incur a loss of thrust due to the opposing pressure of the atmosphere. Multistage rockets are capable of attaining escape velocity from Earth and therefore can achieve unlimited maximum altitude. Compared with airbreathing engines, rockets are lightweight and powerful and capable of generating large accelerations. To control their flight, rockets rely on momentum, airfoils, auxiliary reaction engines, gimballed thrust, momentum wheels, deflection of the exhaust stream, propellant flow, spin, or gravity. Rockets for military and recreational uses date back to at least 13th-century China. Significa ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Encyclopedia Astronautica
The ''Encyclopedia Astronautica'' is a reference web site on Space exploration, space travel. The encyclopedia includes 79,433 articles with 13,741 illustrations, a comprehensive catalog of missiles, spacecraft, space technology, astronauts, and spaceflight from most countries that have had an active rocket research program. It provides biographies of important pioneers of spaceflight such as Konstantin Tsiolkovsky, Hermann Oberth Robert Goddard (scientist), Robert Goddard. It outlines various concepts of space stations including the NASA Space Shuttle and the Soviet Buran programme. Articles In addition, the encyclopedia contains many comprehensive review articles on specific space topics, among them: * ''Germany'' incl. an extensive list of German missile specialists who worked for USA, USSR and France after World War II. * ''Russia - Early Ballistic Missiles'' with a history of the involvement of German rocket specialists in Soviet rocketry. * ''Russia: The Real Moon Landin ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Liquid-propellant Rocket
A liquid-propellant rocket or liquid rocket uses a rocket engine burning liquid rocket propellant, liquid propellants. (Alternate approaches use gaseous or Solid-propellant rocket , solid propellants.) Liquids are desirable propellants because they have reasonably high density and their combustion products have high Specific impulse, specific impulse (''I''sp). This allows the volume of the propellant tanks to be relatively low. Types Liquid rockets can be monopropellant rockets using a single type of propellant, or bipropellant rockets using two types of propellant. Tripropellant rockets using three types of propellant are rare. Liquid oxidizer propellants are also used in hybrid rockets, with some of the advantages of a solid rocket. Bipropellant liquid rockets use a liquid fuel such as liquid hydrogen or RP-1, and a liquid oxidizer such as liquid oxygen. The engine may be a cryogenic rocket engine, where the fuel and oxidizer, such as hydrogen and oxygen, are gases which hav ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
AJ-10
The AJ10 is a hypergolic rocket engine manufactured by Aerojet Rocketdyne (previously Aerojet). It has been used to propel the upper stages of several launch vehicles, including the Delta II and Titan III. Variants were and are used as the service propulsion engine for the Apollo command and service module, in the Space Shuttle Orbital Maneuvering System, and on the European Service Module – part of NASA's Orion spacecraft. Variants It was first used in the Delta-A/Able second stage of the Vanguard rocket, in the AJ10-37 configuration. It was initially fueled by nitric acid and UDMH. An AJ10 engine was first fired in flight during the third Vanguard launch, on 17 March 1958, which successfully placed the Vanguard 1 satellite into orbit. The AJ10-101 engine was used on an uprated version of the Able stage, used on Atlas-Able and Thor-Able rockets. The first AJ10-101 flight, with a Thor-Able, occurred on 23 April 1958; however, the Thor failed before the upper Able stage fi ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Titan IV
Titan IV was a family of heavy-lift space launch vehicles developed by Martin Marietta and operated by the United States Air Force from 1989 to 2005. Launches were conducted from Cape Canaveral Air Force Station, Florida and Vandenberg Air Force Base, California. The Titan IV was the last of the Titan family of rockets, originally developed by the Glenn L. Martin Company in 1958. It was retired in 2005 due to their high cost of operation and concerns over its toxic hypergolic propellants, and replaced with the Atlas V and Delta IV launch vehicles under the EELV program. The final launch (B-30) from Cape Canaveral occurred on 29 April 2005, and the final launch from Vandenberg AFB occurred on 19 October 2005. Lockheed Martin Space Systems built the Titan IVs near Denver, Colorado, under contract to the US government. Two Titan IV vehicles are currently on display at the National Museum of the United States Air Force in Dayton, Ohio and the Evergreen Aviation and Space Muse ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Titan IIIA
The Titan IIIA or Titan 3A was an American expendable launch system, launched four times in 1964 and 1965, to test the Transtage upper stage which was intended for use on the larger Titan IIIC. The Transtage was mounted atop two core stages derived from the Titan II The Titan II was an intercontinental ballistic missile (ICBM) developed by the Glenn L. Martin Company from the earlier Titan I missile. Titan II was originally designed and used as an ICBM, but was later adapted as a medium-lift space .... The Titan IIIA was also used as the core of the Titan IIIC. Part of the Titan rocket family, the Titan IIIA made its first flight on 1 September 1964. However, the Transtage failed to pressurize, resulting in a premature cutoff and failure to reach orbit. A second test on 10 December was successful. Two further launches occurred in 1965 with Lincoln Experimental Satellites, before the Titan IIIA was retired. Launch history References * * External links T ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Titan II GLV
The Titan II GLV (Titan II Gemini Launch Vehicle) or Gemini-Titan II was an American expendable launch system derived from the Titan II missile, which was used to launch twelve Gemini missions for NASA between 1964 and 1966. Two uncrewed launches followed by ten crewed ones were conducted from Launch Complex 19 at the Cape Canaveral Air Force Station, starting with Gemini 1 on April 8, 1964. The Titan II was a two-stage liquid-fuel rocket, using a hypergolic propellant combination of Aerozine 50 fuel and nitrogen tetroxide oxidizer. The first stage was powered by an LR87 engine (with two combustion chambers and nozzles, fed by separate sets of turbomachinery), and the second stage was propelled by an LR91 engine. Modifications from the Titan II missile In addition to greater payload capability, the Titan II promised greater reliability than the Atlas LV-3B, which had been selected for Project Mercury, because Titan's hypergolic-fueled engines contained far fewer componen ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Hypergolic Propellant
A hypergolic propellant is a rocket propellant combination used in a rocket engine, whose components spontaneously ignite when they come into contact with each other. The two propellant components usually consist of a fuel and an oxidizer. The main advantages of hypergolic propellants are that they can be stored as liquids at room temperature and that engines which are powered by them are easy to ignite reliably and repeatedly. Common hypergolic propellants are extremely toxic or corrosive, making them difficult to handle. In contemporary usage, the terms "hypergol" and "hypergolic propellant" usually mean the most common such propellant combination: dinitrogen tetroxide plus hydrazine. History The fact that turpentine may spontaneously combust when mixed with nitric acid was discovered as early as the late 17th century by Frederick Slare, but it remained a scientific curiosity for centuries until it was proposed to use it for rocket-assisted take off during WWII. In 1935 ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Cryogenic
In physics, cryogenics is the production and behaviour of materials at very low temperatures. The 13th International Institute of Refrigeration's (IIR) International Congress of Refrigeration (held in Washington, DC in 1971) endorsed a universal definition of "cryogenics" and "cryogenic" by accepting a threshold of to distinguish these terms from conventional refrigeration. This is a logical dividing line, since the normal boiling points of the so-called permanent gases (such as helium, hydrogen, neon, nitrogen, oxygen, and normal air) lie below 120 K, while the Freon refrigerants, hydrocarbons, and other common refrigerants have boiling points above 120 K. Discovery of superconducting materials with critical temperatures significantly above the boiling point of nitrogen has provided new interest in reliable, low-cost methods of producing high-temperature cryogenic refrigeration. The term "high temperature cryogenic" describes temperatures ranging from above the ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Titan I
The Martin Marietta SM-68A/HGM-25A Titan I was the United States' first multistage intercontinental ballistic missile (ICBM), in use from 1959 until 1962. Though the SM-68A was operational for only three years, it spawned numerous follow-on models that were a part of the U.S. arsenal and space launch capability. The Titan I was unique among the Titan models in that it used liquid oxygen and RP-1 as propellants; all subsequent versions used storable propellants instead. Originally designed as a backup in case the U.S. Air Force's SM-65 Atlas missile development ran into problems, the Titan was ultimately beaten into service by Atlas. Deployment went ahead anyway to more rapidly increase the number of missiles on alert and because the Titan's missile silo basing was more survivable than Atlas. The succeeding LGM-25C Titan II served in the U.S. nuclear deterrent until 1987 and had increased capacity and range in addition to the different propellants. History By January 1955, the ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
