"for all of the Saturn support facilities at MSFC. SA-500D is the only Saturn V on display that was used for its intended purpose, and the only one to have been assembled prior to museum display. It is on permanent display at the U.S. Space & Rocket Center, Huntsville, Alabama. Before a Saturn V could launch, engineers needed to verify that their design had accounted for everything the rocket would encounter on its journey, from assembly to the launchpad and from Earth to the Moon. To validate the Saturn V design and procedures, they created five pre-flight configurations for testing."
"S-IC The S-IC (pronounced ""ess one see"") was the first stage of the American Saturn V rocket. The S-IC stage was built by the Boeing Company. Like the first stages of most rockets, most of its mass of more than 2,000 tonnes at launch was propellant, in this case RP-1 rocket fuel and liquid oxygen (LOX) oxidizer. It was 42 meters tall and 10 meters in diameter, and provided 33,000 kN of thrust to get the rocket through the first 61 kilometers of ascent. The stage had five F-1 engines in a quincunx arrangement. The center engine was fixed in"
"Saturn V The Saturn V (pronounced ""Saturn five"") was an American human-rated expendable rocket used by NASA between 1967 and 1973. The three-stage liquid-propellant super heavy-lift launch vehicle was developed to support the Apollo program for human exploration of the Moon and was later used to launch Skylab, the first American space station. The Saturn V was launched 13 times from the Kennedy Space Center in Florida with no loss of crew or payload. the Saturn V remains the tallest, heaviest, and most powerful (highest total impulse) rocket ever brought to operational status, and holds records for the heaviest payload"
"of the fairings forward of the fins, and backing the S-IC away from the flight vehicle as the engines on the S-II stage were ignited. It also carried the ODOP transponder to track the flight after takeoff. S-IC The S-IC (pronounced ""ess one see"") was the first stage of the American Saturn V rocket. The S-IC stage was built by the Boeing Company. Like the first stages of most rockets, most of its mass of more than 2,000 tonnes at launch was propellant, in this case RP-1 rocket fuel and liquid oxygen (LOX) oxidizer. It was 42 meters tall and"
"the Saturn V. The objectives of the mission were to: The mission profile called for the Saturn IB to launch the spacecraft on an east-by-southeast heading into a high ballistic trajectory; then the CSM would separate from the SLA. The service module engine would be fired twice, then the command module would re-enter and land in the south Atlantic Ocean. The first piece of the rocket to arrive at the Cape was the S-IB stage on August 14, 1965, by the barge ""Promise"". It was built by Chrysler and featured eight H-1 engines built by Rocketdyne. The S-IVB second stage"
"1972 the site was utilized by Chrysler Corporation to build the first stages of the Saturn I and Saturn IB, later joined by Boeing Corporation to build the first stage of the Saturn V rockets. From September 5, 1973, to September 20, 2010, the factory was used for the construction of the Space Shuttle's external fuel tanks by Martin Marietta Corporation, Denver Colorado. The facility was originally constructed in 1940 at the village of Michoud, Louisiana, by the Higgins-Tucker division of Higgins Industries under the direction of Andrew Jackson Higgins. Construction was done on behalf of the United States government"
"Saturn V Dynamic Test Vehicle Saturn V Dynamic Test Vehicle, designated SA-500D, is a prototype Saturn V rocket used by NASA to test the performance of the rocket when vibrated to simulate the shaking which subsequent rockets would experience during launch. It was the first full-scale Saturn V completed by the Marshall Space Flight Center (MSFC). Though SA-500D never flew, it was instrumental in the development of the Saturn V rocket which propelled the first men to the Moon as part of the Apollo program. Built under the direction of Dr. Wernher von Braun, it served as the test vehicle"
"Rocketdyne F-1 The F-1 is a gas-generator cycle rocket engine developed in the United States by Rocketdyne in the late 1950s and used in the Saturn V rocket in the 1960s and early 1970s. Five F-1 engines were used in the S-IC first stage of each Saturn V, which served as the main launch vehicle of the Apollo program. The F-1 remains the most powerful single combustion chamber liquid-propellant rocket engine ever developed. Rocketdyne developed the F-1 and the E-1 to meet a 1955 U.S. Air Force requirement for a very large rocket engine. The E-1, although successfully tested in"
"Instrument Unit. Saturn V Dynamic Test Vehicle Saturn V Dynamic Test Vehicle, designated SA-500D, is a prototype Saturn V rocket used by NASA to test the performance of the rocket when vibrated to simulate the shaking which subsequent rockets would experience during launch. It was the first full-scale Saturn V completed by the Marshall Space Flight Center (MSFC). Though SA-500D never flew, it was instrumental in the development of the Saturn V rocket which propelled the first men to the Moon as part of the Apollo program. Built under the direction of Dr. Wernher von Braun, it served as the"
"launched and largest payload capacity to low Earth orbit (LEO) of , which included the third stage and unburned propellant needed to send the Apollo Command/Service Module and Lunar Module to the Moon. The largest production model of the Saturn family of rockets, the Saturn V was designed under the direction of Wernher von Braun and Arthur Rudolph at the Marshall Space Flight Center in Huntsville, Alabama, with Boeing, North American Aviation, Douglas Aircraft Company, and IBM as the lead contractors. , the Saturn V remains the only launch vehicle to carry humans beyond low Earth orbit. A total of"
"Saturn (rocket family) The Saturn family of American rocket boosters was developed by a team of mostly German rocket scientists led by Wernher von Braun to launch heavy payloads to Earth orbit and beyond. Originally proposed as a military satellite launcher, they were adopted as the launch vehicles for the Apollo moon program. Three versions were built and flown: Saturn I, Saturn IB, and Saturn V. The Saturn name was proposed by von Braun in October 1958 as a logical successor to the Jupiter series as well as the Roman god's powerful position. In 1963, president John F. Kennedy identified"
"awarded the Ares I Upper Stage manufacturing contract to Boeing. Boeing built the S-IC stage of the Saturn V rocket at Michoud Aerospace Factory in the 1960s. The upper stage of Ares I was to have been built at the same rocket factory used for the Space Shuttle's External Tank and the Saturn V's S-IC first stage. At approximately US$20–25 million per engine, the Rocketdyne-designed and produced J-2X would have cost less than half as much as the more complex Space Shuttle Main Engine (around $55 million). Unlike the Space Shuttle Main Engine, which was designed to start on the"
"S-II The S-II (pronounced ""S-two"") was the second stage of the Saturn V rocket. It was built by North American Aviation. Using liquid hydrogen (LH2) and liquid oxygen (LOX) it had five J-2 engines in a quincunx pattern. The second stage accelerated the Saturn V through the upper atmosphere with of thrust. The beginning of the S-II came in December 1959 when a committee recommended the design and construction of a high-thrust, liquid hydrogen fueled engine. The contract for this engine was given to Rocketdyne and it would be later called the J-2. At the same time the S-II stage"
"mission, as well as a gas generator from an engine that powered the Apollo 16 flight. Rocketdyne F-1 The F-1 is a gas-generator cycle rocket engine developed in the United States by Rocketdyne in the late 1950s and used in the Saturn V rocket in the 1960s and early 1970s. Five F-1 engines were used in the S-IC first stage of each Saturn V, which served as the main launch vehicle of the Apollo program. The F-1 remains the most powerful single combustion chamber liquid-propellant rocket engine ever developed. Rocketdyne developed the F-1 and the E-1 to meet a 1955"
"At in height, the entire Saturn V could be accommodated. Also completed in 1964, the S1C Static Test Stand was for live firing of the five F-1 engines of the first stage. Delivering a total of 7.5-million-pounds thrust, the tests produced earthquake-like rumbles throughout the Huntsville area and could be heard as far as away. As the Saturn activities progressed, external facilities were needed. In 1961, The Michoud Rocket Factory near New Orleans, Louisiana, was selected as the Saturn production site. A isolated area in Hancock County, Mississippi was selected to conduct Saturn tests. Known as the Mississippi Test Facility"
"S-IV The S-IV was the second stage of the Saturn I rocket used by NASA for early flights in the Apollo program. The S-IV was manufactured by the Douglas Aircraft Company and later modified by them to the S-IVB, a similar but distinct stage used on the Saturn IB and Saturn V rockets. The S-IV stage was a large LOX/LH-fueled rocket stage used for the early test flights of the Saturn I rocket. It formed the second stage of the Saturn I and was powered by a cluster of six RL-10A-3 engines. Each one of the engines supplied of thrust"
"fueled Saturn V exploding on the pad would have released the energy equivalent of two kilotons of TNT. To improve safety, the Saturn Emergency Detection System (EDS) inhibited engine shutdown for the first 30 seconds of flight. (See Saturn V Instrument Unit) It took about 12 seconds for the rocket to clear the tower. During this time, it yawed 1.25 degrees away from the tower to ensure adequate clearance despite adverse winds. (This yaw, although small, can be seen in launch photos taken from the east or west.) At an altitude of the rocket rolled to the correct flight azimuth"
"in the Redstone). They are descendants of the LEV-3 of the German V-2 rocket. The ST-124 was designed by Marshall Space Flight Center and manufactured by Bendix Corporation, Eclipse-Pioneer Division, in Teterboro, NJ. It took 9 men 22 to 24 weeks to assemble an ST-124, and 70 percent of that time was spent installing about 3,000 wires. The ST-124 stabilized platform was part of the navigation, control and guidance system of the Saturn V. Data from the ST-124 were used by the Launch Vehicle Digital Computer (another Instrument Unit component) to compare actual flight data to programmed flight plans and"
"most powerful single-nozzle liquid-fueled rocket engine ever used in service; each produced 1.5-million-pounds thrust. Originally started by the U.S. Air Force, responsibility for the development was taken over by ABMA in 1959, and the first test firings at MSFC were in December 1963. The original vehicle, designated Saturn I, consisted of two propulsion stages and an instrument unit; it was first tested in flight on October 27, 1961. The first stage (S-I) had a cluster of eight H-1 engines, giving approximately 1.5-million-pounds thrust total. The four outboard engines were gimbaled to allow vehicle steering. The second stage (SIV) had six"
"complete Saturn V at the Kennedy Space Center in Florida. SA-500D, the Dynamic Test Vehicle, is on display at the U.S. Space and Rocket Center in Huntsville, Alabama. A test engine is on display at the Powerhouse Museum in Sydney, Australia. It was the 25th out of 114 research and development engines built by Rocketdyne and it was fired 35 times. The engine is on loan to the museum from the Smithsonian's National Air and Space Museum. It is the only F-1 on display outside the United States. An F-1 engine, on loan from the National Air and Space Museum,"
"firing the spacecraft into trans-lunar space). S-IVB The S-IVB (sometimes S-4B, always pronounced ""ess four bee"") was built by the Douglas Aircraft Company and served as the third stage on the Saturn V and second stage on the Saturn IB. It had one J-2 engine. For lunar missions it was fired twice: first for the orbit insertion after second stage cutoff, and then for translunar injection (TLI). The S-IVB evolved from the upper stage of the Saturn I rocket, the S-IV, and was the first stage of the Saturn V to be designed. The S-IV used a cluster of six"
"stage. Five F-1 engines powered the Saturn V's, S-IC, first stage, while five J-2 engines powered its S-II second stage, and one J-2 the S-IVB third stages. By 1965, Rocketdyne built the vast majority of US rocket engines, excepting those of the Titan rocket, and its payroll had grown to 65,000. This sort of growth appeared to be destined to continue in the 1970s when Rocketdyne won the contract for the Space Shuttle Main Engine. But the rapid downturn in other military and civilian contracts led to downsizing of the company. North American Aviation, largely a spacecraft manufacturer, and also"
"NASA at Marshall Space Flight Center (MSFC) and was developed from the Saturn I IU. NASA's contractor to manufacture the Saturn V Instrument Unit was International Business Machines (IBM). One of the unused instrument units is currently on display at the Steven F. Udvar-Hazy Center in Chantilly, Virginia. The plaque for the unit has the following inscription: The Saturn V rocket, which sent astronauts to the Moon, used inertial guidance, a self-contained system that guided the rocket's trajectory. The rocket booster had a guidance system separate from those on the command and lunar modules. It was contained in an instrument"
"the capabilities of the Saturn family. NASA specified a LEO of , 28° inclination for payload calculations, and the studies examined a number of Modified Launch Vehicle (MLV) configurations based on the Saturn IB and Saturn V launch vehicles as well as Intermediate Payload (INT) launch vehicles based on modified Saturn V stages (MS-IC, MS-II, and MS-IVB). Martin Marietta (builder of Atlas and Titan rockets), Boeing (builder of S-IC first stages), and North American Aviation (builder of the S-II second stage) were three of the companies that provided responses. North American considered the best way to fill the gap was"
"Shuttle and Saturn V hardware and infrastructure. The two rockets were intended to increase safety by specializing each vehicle for different tasks, Ares I for crew launches and Ares V for cargo launches. The original design of the heavy-lift Ares V, named in homage to the Saturn V, was in height and featured a core stage based on the Space Shuttle External Tank, with a diameter of . It was to be powered by five Space Shuttle Main Engines (SSMEs) and two five-segment Space Shuttle Solid Rocket Boosters (SRBs). As the design evolved, the SSMEs were replaced with five RS-68"
"Flight Center decided to use the C-5 rocket (later called the Saturn V), which had three stages and would be topped with an uprated S-IV called the S-IVB which instead of using a cluster of engines would have a single J-2 engine. Douglas was awarded the contract for the S-IVB because of the similarities between it and the S-IV. At the same time it was decided to create the C-IB rocket (Saturn IB) that would also use the S-IVB as its second stage and could be used for testing the Apollo spacecraft in Earth orbit. Douglas built two distinct versions"
"for a total of about . The cryogenic LH (liquid hydrogen) and LOX (liquid oxygen) tanks were separated by a common bulkhead. The forward bulkhead of the LOX tank formed the aft bulkhead of the LH tank. This saved up to 20% of structural weight. S-IV The S-IV was the second stage of the Saturn I rocket used by NASA for early flights in the Apollo program. The S-IV was manufactured by the Douglas Aircraft Company and later modified by them to the S-IVB, a similar but distinct stage used on the Saturn IB and Saturn V rockets. The S-IV"
"equivalents. Saturn makes the AL-31 turbojet which powers China's Chengdu J-10 multirole jet fighter aircraft. , Saturn VMF ""RUSSKAYA MEKHANIKA“ company is the manufacturer of snowmobiles TAJGA and BURAN, Approximately 10000 of these units come from the plant each year. It is a 100% affiliated company of NPO SATURN. The snowmobiles have been produced in Rybinsk in the Yaroslavl Oblast. (approx. 400 km north of Moscow) since 1971. UEC Saturn UEC NPO Saturn, PJSC () is a Russian aircraft engine manufacturer, formed from the mergers of Rybinsk Motors and Lyul'ka-Saturn (after Arkhip Mikhailovich Lyulka) in 2001. Saturn's engines power many"
"produced. Some other recent US launch vehicles have significantly lower launch capacity to LEO than Saturn V: the US Delta 4 Heavy capacity is , the Atlas V 551 has a capacity of , and the SpaceX Falcon Heavy has a capacity of . The European Ariane 5 ES delivers up to and the Russian Proton-M can launch . NASA's Space Launch System, planned for its first flight in 2020, in its final configuration is planned to be tall with payload, and lift up to into low Earth orbit. Because of its large size, attention is often focused on the"
"Big Ben clock tower. In contrast, the Mercury-Redstone Launch Vehicle used on ""Freedom 7"", the first manned American spaceflight, was just under longer than the S-IVB stage, and delivered less sea level thrust () than the Launch Escape System rocket ( sea level thrust) mounted atop the Apollo Command Module. The Saturn V was principally designed by the Marshall Space Flight Center in Huntsville, Alabama, although numerous major systems, including propulsion, were designed by subcontractors. It used the powerful new F-1 and J-2 rocket engines for propulsion. When tested at Stennis Space Center, these engines shattered the windows of nearby"
"S-IVB The S-IVB (sometimes S-4B, always pronounced ""ess four bee"") was built by the Douglas Aircraft Company and served as the third stage on the Saturn V and second stage on the Saturn IB. It had one J-2 engine. For lunar missions it was fired twice: first for the orbit insertion after second stage cutoff, and then for translunar injection (TLI). The S-IVB evolved from the upper stage of the Saturn I rocket, the S-IV, and was the first stage of the Saturn V to be designed. The S-IV used a cluster of six engines but used the same fuels"
"on by hand and trim the excess. This change saved both weight and time and avoided the issues with air pockets entirely. The LH2 tank volume was 1182 cu.m. (260,000 gal.) for storing 69,400 kg (153,000 lbs) of liquid hydrogen. The S-II was constructed vertically to aid welding and keep the large circular sections in the correct shape. S-II The S-II (pronounced ""S-two"") was the second stage of the Saturn V rocket. It was built by North American Aviation. Using liquid hydrogen (LH2) and liquid oxygen (LOX) it had five J-2 engines in a quincunx pattern. The second stage accelerated"
"of the standard Saturn V and were intended for use in a proposed mission to Mars by 1980. In 1968, Boeing studied another Saturn-V derivative, the Saturn C-5N, which included a nuclear thermal rocket engine for the third stage of the vehicle. The Saturn C-5N would carry a considerably greater payload to interplanetary destinations. Work on the nuclear engines, along with all Saturn V ELVs, was ended in 1973. In 2006, as part of the proposed Constellation Program, NASA unveiled plans to construct two Shuttle Derived Launch Vehicles, the Ares I and Ares V, which would use some existing Space"