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RS-27
The RS-27 was a liquid-propellant rocket engine developed in 1974 by Rocketdyne to replace the aging MB-3 in the Delta. Incorporating components of the venerable MB-3 and the H-1 designs, the RS-27 was a modernized version of the basic design used for two decades. It was used to power the first stage of the Delta 2000, 3000, 5000, and the first model of the Delta II, the Delta 6000. The RS-27 was a modified Rocketdyne H-1 built to power the first stage of the Saturn I The Saturn I was a rocket designed as the United States' first medium lift launch vehicle for up to low Earth orbit payloads.Terminology has changed since the 1960s; back then, 20,000 pounds was considered "heavy lift". The rocket's first sta ... and Saturn IB and replaced the MB-3 engine that had been used on previous versions of the Delta launcher. NASA had a large supply of surplus H-1 engines in the early 1970s, as the Apollo program was ending. In addition to its main engine, the RS-27 included ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
RS-27A
The RS-27A is a liquid-fuel rocket engine developed in 1980s by Rocketdyne for use on the first stage of the Delta II and Delta III launch vehicles. It provides of thrust burning RP-1 and LOX in a gas-generator cycle. The engine is a modified version of its predecessor, the RS-27 The RS-27 was a liquid-propellant rocket engine developed in 1974 by Rocketdyne to replace the aging MB-3 in the Delta. Incorporating components of the venerable MB-3 and the H-1 designs, the RS-27 was a modernized version of the basic design ...; its thrust nozzle has been extended to increase its area ratio from 8:1 to 12:1, which provides greater efficiency at altitude. The RS-27A main engine is neither restartable nor throttleable. In addition to its main engine, it includes two vernier engines to provide vehicle roll control during flight.. When used as the main booster propulsion system for the Delta II family of launch vehicles, has an operational duration of 265 seconds. The last RS-27A ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Delta II
Delta II was an expendable launch system, originally designed and built by McDonnell Douglas. Delta II was part of the Delta rocket family and entered service in 1989. Delta II vehicles included the Delta 6000, and the two later Delta 7000 variants ("Light" and "Heavy"). The rocket flew its final mission ICESat-2 on 15 September 2018, earning the launch vehicle a streak of 100 successful missions in a row, with the last failure being GPS IIR-1 in 1997. History In the early 1980s, all United States expendable launch vehicles were planned to be phased out in favor of the Space Shuttle, which would be responsible for all government and commercial launches. Production of Delta, Atlas-Centaur, and Titan 34D had ended. The ''Challenger'' disaster of 1986 and the subsequent halt of Shuttle operations changed this policy, and President Ronald Reagan announced in December 1986 that the Space Shuttle would no longer launch commercial payloads, and NASA would seek to purchase la ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Delta (rocket Family)
Delta is an American versatile family of expendable launch systems that has provided space launch capability in the United States since 1960. Japan also launched license-built derivatives ( N-I, N-II, and H-I) from 1975 to 1992. More than 300 Delta rockets have been launched with a 95% success rate. Only the Delta IV Heavy rocket remains in use as of November 2020. Delta rockets have stopped being manufactured in favor of Vulcan. Origins The original Delta rockets used a modified version of the PGM-17 Thor, the first ballistic missile deployed by the United States Air Force (USAF), as their first stage. The Thor had been designed in the mid-1950s to reach Moscow from bases in Britain or similar allied nations, and the first wholly successful Thor launch had occurred in September 1957. Subsequent satellite and space probe flights soon followed, using a Thor first stage with several different upper stages. The fourth upper stage used on the Thor was the Thor "Delta", del ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Rocketdyne
Rocketdyne was an American rocket engine design and production company headquartered in Canoga Park, in the western San Fernando Valley of suburban Los Angeles, in southern California. The Rocketdyne Division was founded by North American Aviation (NAA) in 1955, and was later part of Rockwell International (1967–1996) and Boeing (1996–2005). In 2005, the Rocketdyne Division was sold to United Technologies Corporation, becoming Pratt & Whitney Rocketdyne as part of Pratt & Whitney. In 2013, Pratt & Whitney Rocketdyne was sold to GenCorp, which merged it with Aerojet to form Aerojet Rocketdyne.Marjorie Censer(18 Dec 2022) L3Harris moves to acquire Aerojet Rocketdynefor $4.7 billion, after Lockheed Martin ended its attempt for Rocketdyne in Feb 2022 History After World War II, North American Aviation (NAA) was contracted by the Defense Department to study the German V-2 missile and adapt its engine to Society of Automotive Engineers (SAE) measurements and U.S. const ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Rocketdyne Engines
Rocketdyne was an American rocket engine design and production company headquartered in Canoga Park, in the western San Fernando Valley of suburban Los Angeles, in southern California. The Rocketdyne Division was founded by North American Aviation (NAA) in 1955, and was later part of Rockwell International (1967–1996) and Boeing (1996–2005). In 2005, the Rocketdyne Division was sold to United Technologies Corporation, becoming Pratt & Whitney Rocketdyne as part of Pratt & Whitney. In 2013, Pratt & Whitney Rocketdyne was sold to GenCorp, which merged it with Aerojet to form Aerojet Rocketdyne.Marjorie Censer(18 Dec 2022) L3Harris moves to acquire Aerojet Rocketdynefor $4.7 billion, after Lockheed Martin ended its attempt for Rocketdyne in Feb 2022 History After World War II, North American Aviation (NAA) was contracted by the Defense Department to study the German V-2 missile and adapt its engine to Society of Automotive Engineers (SAE) measurements and U.S. const ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Delta 2000
The Delta 2000 series was an American expendable launch system which was used to conduct forty-four orbital launches between 1974 and 1981. It was a member of the Delta family of rockets. Several variants existed, which were differentiated by a four digit numerical code. The Delta 1000, 2000 and 3000 series used surplus NASA Apollo program rockets engines for its first and second stages. The first stage was an Extended Long Tank Thor, re-engined with the Rocketdyne RS-27 replacing the earlier MB-3-III engine. The RS-27 engine was a rebranded H-1 engine used in the Saturn 1B with minor changes. Three or nine Castor-2 solid rocket boosters were attached to increase thrust at lift-off. The Delta-P second stage used the TRW TR-201 engine. The TR-201 engine was a Lunar Module Descent Engine reconfigured for fixed thrust output. Launches which required a three-stage configuration in order to reach higher orbits used the Thiokol Star-37D or Star-37E upper stage as an apogee kick ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Rocketdyne H-1
The Rocketdyne H-1 was a thrust liquid-propellant rocket engine burning LOX and RP-1. The H-1 was developed for use in the S-I and S-IB first stages of the Saturn I and Saturn IB rockets, respectively, where it was used in clusters of eight engines. After the Apollo program, surplus H-1 engines were rebranded and reworked as the Rocketdyne RS-27 engine with first usage on the Delta 2000 series in 1974. The RS-27 variant is also used on the Delta II and Delta III. History Early engines The H-1 is one of a series of engines developed from the wartime V-2 ballistic missile. During the war, North American Aviation (NAA) was given several V-2 engines to examine and convert from metric to SAE measurements. They formed their "Propulsion Division" to handle this work, later becoming Rocketdyne. NAA had also been given a wealth of technical documentation on the engine. Engineers studying them came across plans to improve the V-2 engine using a new "waterfall" fuel injector. The ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
RS-56
RS-56 was an American liquid-fueled rocket engine, developed by Rocketdyne. RS-56 was derived from the RS-27 rocket engine, which itself is derived from the Rocketdyne H-1 rocket engine used in the Saturn I and Saturn IB. Two variants of this engine were built, both for use on the Atlas II rocket series. The first, RS-56-OBA, was a booster engine, while the RS-56-OSA was designed for use as a sustainer and produced lower thrust but at a higher specific impulse Specific impulse (usually abbreviated ) is a measure of how efficiently a reaction mass engine (a rocket using propellant or a jet engine using fuel) creates thrust. For engines whose reaction mass is only the fuel they carry, specific impulse is .... References {{Rocket engines Rocketdyne engines Rocket engines using the gas-generator cycle Rocket engines using kerosene propellant Rocket engines of the United States ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Gas-generator Cycle (rocket)
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 * 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 combu ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Rocket Engines Using The Gas-generator Cycle
A rocket (from it, rocchetto, , bobbin/spool) is a vehicle that uses jet propulsion to accelerate without using the 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. Significant ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Vernier Thruster
A vernier thruster is a rocket engine used on a spacecraft for fine adjustments to the attitude or velocity of a spacecraft. Depending on the design of a craft's maneuvering and stability systems, it may simply be a smaller thruster complementing the main propulsion system, or it may complement larger attitude control thrusters, or may be a part of the reaction control system. The name is derived from vernier calipers (named after Pierre Vernier) which have a primary scale for gross measurements, and a secondary scale for fine measurements. Vernier thrusters are used when a heavy spacecraft requires a wide range of different thrust levels for attitude or velocity control, as for maneuvering during docking with other spacecraft. On space vehicles with two sizes of attitude control thrusters, the main ACS (Attitude Control System) thrusters are used for larger movements, while the verniers are reserved for smaller adjustments. Due to their weight and the extra plumbing required ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Saturn IB
The Saturn IB (also known as the uprated Saturn I) was an American launch vehicle commissioned by the National Aeronautics and Space Administration (NASA) for the Apollo program. It uprated the Saturn I by replacing the S-IV second stage (, 43,380,000 lb-sec total impulse), with the S-IVB (, 96,000,000 lb-sec total impulse). The S-IB first stage also increased the S-I baseline's thrust from to and propellant load by 3.1%. This increased the Saturn I's low Earth orbit payload capability from to , enough for early flight tests of a half-fueled Apollo command and service module (CSM) or a fully fueled Apollo Lunar Module (LM), before the larger Saturn V needed for lunar flight was ready. By sharing the S-IVB upper stage, the Saturn IB and Saturn V provided a common interface to the Apollo spacecraft. The only major difference was that the S-IVB on the Saturn V burned only part of its propellant to achieve Earth orbit, so it could be restarted for trans-lunar inj ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
