"production would have allowed the International Space Station, using a Skylab or Mir configuration with both U.S. and Russian docking ports, to have been lifted with just a handful of launches. The Saturn-Shuttle concept also would have eliminated the Space Shuttle Solid Rocket Boosters that ultimately precipitated the ""Challenger"" accident in 1986. From 1964 until 1973, $6.417 billion (equivalent to $ in ) in total was appropriated for the R&D and flights of the Saturn V, with the maximum being in 1966 with $1.2 billion (equivalent to $ in ). That same year, NASA received its biggest budget of $4.5"
"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"
"the Saturn V. The Saturn V used higher-specific impulse liquid hydrogen fuel in the second and third stages, which eliminated one of the stages needed to get to translunar injection, thus saving weight. The second stage, Block B, was powered by 8 NK-15V engines arranged in a single ring. The only major difference between the NK-15 and -15V was the engine bell and various tunings for air-start and high-altitude performance. The upper stage, Block V (В/""V"" being the third letter in the Russian alphabet), mounted four smaller NK-21 engines in a square. During the N1's lifetime, a series of improved"
"de Laval nozzle-type J-2S and aerospike-type J-2T, which were cancelled after the conclusion of the Apollo program. The engine produced a specific impulse (""I"") of in a vacuum (or at sea level) and had a mass of approximately . Five J-2 engines were used on the Saturn V's S-II second stage, and one J-2 was used on the S-IVB upper stage used on both the Saturn IB and Saturn V. Proposals also existed to use various numbers of J-2 engines in the upper stages of an even larger rocket, the planned Nova. The J-2 was America's largest production LH2-fuelled rocket"
"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"
"Earth orbit, sufficient for a partially fueled CSM or the LM. Saturn IB launch vehicles and flights were designated with an AS-200 series number, ""AS"" indicating ""Apollo Saturn"" and the ""2"" indicating the second member of the Saturn rocket family. Saturn V launch vehicles and flights were designated with an AS-500 series number, ""AS"" indicating ""Apollo Saturn"" and the ""5"" indicating Saturn V. The three-stage Saturn V was designed to send a fully fueled CSM and LM to the Moon. It was in diameter and stood tall with its lunar payload. Its capability grew to for the later advanced lunar"
"was developed as the Saturn V launch vehicle. The S-IV, later flown on the Saturn I, was to serve as the third C-2 stage and fourth C-3 stage; and an S-V Centaur (rocket stage) would be the fourth C-2 stage. While this S-V/Centaur stage would never fly on any Saturn rockets, it would be used on Atlas and Titan launch vehicles. The Centaur is still in use on the Atlas V and the derived Delta Cryogenic Second Stage (DCSS) on the Delta IV. The Advanced Common Evolved Stage is the latest proposed derivative as an upper stage replacement for the"
"version was the Saturn A-1, which had the familiar S-I stage plus a Titan I 1st stage as a 2nd stage and a Centaur as a 3rd stage. The Saturn A-2 was the same except that the 2nd stage consisted of a cluster of 4 Jupiters rather than a Titan 1st stage. In the Saturn B-1, the 2nd stage was a custom-developed LOX/RP-1 stage powered by 4 H-1 engines. Again, the Centaur was to be the 3rd stage. Then there was the Saturn C-1: S-I stage plus S-IV plus Centaur, known in this application as the S-V. This is the"
"( vs. ). The N1 produced more thrust in each of its three stages than the Saturn V. It also produced more total impulse in its first four stages than the Saturn V did in its three (see table below). The N1 was intended to place the ≈ L3 payload into low Earth orbit, whereas the Saturn V placed the roughly Apollo spacecraft, plus of fuel for translunar injection, into Earth parking orbit. L3 translunar injection of a payload was to be provided by the fourth stage. The N1-L3 would have been able to convert only 9.3% of its three-stage"
"and payload standpoint. The Saturn V consisted of three propulsion stages and an instrument unit. The first stage (S-IC), had five F-1 engines, giving a combined total of 7.5-million-pounds thrust. These engines were arranged in a cross pattern, with the center engine fixed and the outer four gimballed. The second stage (S-II), had five J-2 engines with the same arrangement as the F-1s and giving a total of 1.0-million-pounds thrust. The third stage (S-IVB) had a single gimballed J-2 engine with 200-thousand-pounds thrust. As previously noted, the J-2 engine could be restarted in flight. The basic configuration for this heavy-lift"
"of the S-IVB, the 200 series and the 500 series. The 200 series was used by the Saturn IB and differed from the 500 in that it did not have a flared interstage and it had less helium pressurization on board since it did not have to be restarted. In the 500 series, the interstage needed to flare out to match the larger diameter of the S-IC and S-II stages of the Saturn V. The 200 series also had three solid rockets for separating the S-IVB stage from the S-IB stage during launch. On the 500 series this was reduced"
"V, ranging from the Saturn INT-20 with an S-IVB stage and interstage mounted directly onto an S-IC stage, through to the Saturn V-23(L) which would not only have five F-1 engines in the first stage, but also four strap-on boosters with two F-1 engines each: giving a total of thirteen F-1 engines firing at launch. The Space Shuttle was initially conceived as a cargo transport to be used in concert with the Saturn V, even to the point that a Saturn-Shuttle was proposed, using the winged shuttle orbiter and external tank, but with the tank mounted on a modified, fly-back"
"total impulse into Earth orbit payload momentum (compared to 12.14% for the Saturn V), and only 3.1% of its four-stage total impulse into translunar payload momentum, compared to 6.2% for the Saturn V. The N1-L3 used only kerosene-based rocket fuel in all three of its stages, while the Saturn V used liquid hydrogen to fuel its second and third stages, which yielded an overall performance advantage due to the higher specific impulse. The N1 also wasted available propellant volume by using spherical propellant tanks under its conical-shaped external skin, while the Saturn V used most of its available cylindrical skin"
"triggered by external events. For a Saturn IB these interrupts were: For a Saturn V these interrupts were: The LVDC was approximately 30 inches wide, 12.5 inches high, and 10.5 inches deep and weighed 80 pounds. The chassis was made of magnesium-lithium alloy LA 141, chosen for its high stiffness, low weight, and good vibration damping characteristics. The chassis was divided into a 3 x 5 matrix of cells separated by walls through which coolant was circulated to remove the 138 Watts of power dissipated by the computer. Slots in the cell walls held ""pages"" of electronics. The decision to"
"S-II-2 and S-IVB-2 stages intended for use on the Saturn MLV, Saturn IB-B and Saturn V/4-260 rockets, with a sea-level optimised version, the HG-3-SL, intended for use on the Saturn INT-17. The engine was cancelled, however, during the post-Apollo drawdown when development of the more advanced Saturn rockets ceased, and never flew, although the engine was later used as the basis for the design of the RS-25 Space Shuttle main engine. HG-3 (rocket engine) The HG-3 was a liquid-fuel cryogenic rocket engine which was designed for use on the upper stages of Saturn rockets in the post-Apollo era. Designed in"
"stage and Instrument Unit computer arriving the same day. The S-II second stage was two months behind them and so was substituted with a dumbbell-shaped spacer so testing could proceed. This had the same height and mass as the S-II along with all the electrical connections. The S-II arrived May 24. It was stacked and mated into the rocket on July 7. Testing was slow as they were still checking out the launch vehicle for Apollo 4, a limitation of the system where there wasn't two of everyone and everything. The VAB could handle up to four Saturn Vs, but"
"version of the Saturn V second stage S-II-T ruptured during pressure tests at SSC on 28 May 1966, and five North American Aviation technicians monitoring the test received minor injuries. The accident occurred when the hydrogen fuel tank failed under pressure. S-II-T, which had five hydrogen-oxygen J-2 engines capable of generating one million pounds of thrust, had been tested May 25 in ground firing but stopped firing after 195 seconds when a hydrogen link leak caused automatic cutoff. At time of the explosion, technicians were trying to determine cause for the hydrogen leak. No hydrogen was in the tank when"
"probably was the leading proponent in using the Saturn V, and I lost. Probably very wise that I lost."" The canceled second production run of Saturn Vs would very likely have used the F-1A engine in its first stage, providing a substantial performance boost. Other likely changes would have been the removal of the fins (which turned out to provide little benefit when compared to their weight); a stretched S-IC first stage to support the more powerful F-1As; and uprated J-2s or an M-1 for the upper stages. A number of alternate Saturn vehicles were proposed based on the Saturn"
"Atlas V, Delta IV, and Space Launch System. Saturn C-2 The Saturn C-2 was the second rocket in the Saturn C series studied from 1959 to 1962. The design was for a four-stage launch vehicle that could launch 21,500 kg (47,300 lb) to low Earth orbit and send 6,800 kg (14,900 lb) to the Moon via Trans-Lunar Injection. <br>The C-2 design concept was for a proposed manned circumlunar flight and the Earth orbit rendezvous (EOR) missions. It was initially considered for the Apollo lunar landing at the earliest possible date (1967). On September 30, 1960 the fourth meeting of the"
"diameter of and was also designed with high mass efficiency, though not quite as aggressively as the S-II. The S-IVB had a dry weight of about and, fully fueled, weighed about . The S-IVB-500 model used on the Saturn V differed from the S-IVB-200 used as the second stage of the Saturn IB, in that the engine was restartable once per mission. This was necessary as the stage would be used twice during a lunar mission: first in a 2.5 min burn for the orbit insertion after second stage cutoff, and later for the trans-lunar injection (TLI) burn, lasting about"
"stage, and the non-restartable S-IVB-200 used on the Saturn IB became the second stage. Such a vehicle could not fly without modification, because the S-II was designed to operate in the near-vacuum of high altitude space. Atmospheric thrust suppression reduced the five Rocketdyne J-2 engines' of vacuum thrust to at sea level, insufficient to lift the weight of the two stages, even without a payload, off of the ground. This required that the S-II be either refit with higher thrust engines, augmented with solid rocket boosters, or both. Another design variable was the amount of the full propellant load carried"
"Saturn I which actually flew, except that the S-V stage was never live. The original Saturn C-2 design would have been S-I stage plus S-III plus S-IV plus, for some missions, S-V. The S-III was to have been a LOX-Hydrogen stage powered by two J-2 engines. The original Saturn C-3 configuration was S-I plus S-II plus S-III plus, for some missions, the S-IV and even S-V. The S-II was to have had four J-2 engines and the S-I would have been upgraded either by increasing the thrust of its eight H-1 engines to 250,000 lb or by replacing the center"
"volume to house capsule-shaped hydrogen and oxygen tanks, with common bulkheads between the tanks in the second and third stages. The Saturn V also had a superior reliability record: it never lost a payload in two development and eleven operational launches, while four N1 development launch attempts all resulted in failure, with two payload losses. Complex plumbing was needed to feed fuel and oxidizer into the clustered arrangement of rocket engines. This proved to be extremely fragile, and was a major factor in the design's launch failures. Furthermore, unlike Kennedy Space Center Launch Complex 39, the N1's Baikonur launch complex"
"F. Gordon, Jr. described Saturn as ""an old man's ride"", with ""a lot more shake-rattle-and-roll"" but milder thrust. Buzz Aldrin and other Apollo 11 astronauts agreed that they could not tell when Saturn liftoff occurred except from instruments, unlike on Titan. The Soviet space program's counterpart to the Saturn V was Sergei Korolev's N1-L3. The Saturn V was taller, heavier, and had greater payload capacity, both to low Earth orbit and to translunar injection. The N-1 was a three-stage launch vehicle with more liftoff thrust and a larger first stage diameter than the Saturn V. It was to carry the"
"in the S-II, and in the S-IVB stage. Before any version could be put into production, work on all Saturn variants was stopped in favor of launching all future payloads from the Space Shuttle. The Saturn INT-17 was the first version of the Saturn II to be considered. It replaced the first stage's five J-2 engines with seven higher thrust HG-3-SL engines, giving of sea level thrust. It would burn a reduced S-II propellant load of in 200 seconds. The vehicle had a LEO payload capability of with a gross weight of . The reduced payload permitted a savings of"
"to the Saturn designs proposed prior to the meeting; the original design using Titan and Centaur upper stages became the A-1, while another model replacing the Titan with cluster of IRBMs became A-2. The B-1 design proposed a new second stage replacing the A-2s cluster with a new four-engine design using the H-1 like the lower stage. Finally there were three C-series models that replaced all of the upper stages with liquid hydrogen ones. The C-1 used the existing S-I clustered lower, adding the new S-IV stage with four new 15,000 to engines, and keeping the two-engine Centaur on top,"
"Saturn. Of course this increase in tankage might not be easy to arrange. NASA actually considered a new S-IVB replacement, the S-N, built to be as physically large as possible while still being able to be built in the VAB. It weighed only 10,429 kg empty and 53,694 kg fueled (suggesting that structural loading is the dominant factor in stage mass, not the tankage). The combination of lower weight and higher performance improved the payload of the Saturn V as a whole from 127,000 kg delivered to low earth orbit (LEO) to 155,000 kg. It is also worth considering the"
"Rocketdyne J-2 The J-2 was a liquid-fuel cryogenic rocket engine used on NASA's Saturn IB and Saturn V launch vehicles. Built in the U.S. by Rocketdyne, the J-2 burned cryogenic liquid hydrogen (LH2) and liquid oxygen (LOX) propellants, with each engine producing of thrust in vacuum. The engine's preliminary design dates back to recommendations of the 1959 Silverstein Committee. Rocketdyne won approval to develop the J-2 in June 1960 and the first flight, AS-201, occurred on 26 February 1966. The J-2 underwent several minor upgrades over its operational history to improve the engine's performance, with two major upgrade programs, the"
"Saturn V-3 The Saturn V-3, also known as the Saturn MLV 5-3, was a conceptual heavy-lift launch vehicle that would have utilized new engines and new stages that were never used on the original Saturn V. The Saturn V-3 was studied by the NASA Marshall Space Flight Center in 1965. The first stage was to have used new F-1 engines designated F-1A which utilized a pump-fed design, an anticipated 20% additional thrust, and a six-second improvement in specific impulse on an F-1, with the first stage stretched 20 feet. The second and third stages were proposed to use new HG-3"
"roll, pitch, and yaw, and one for ullage), and these were fueled by a hypergolic mixture of dinitrogen tetroxide and monomethyl hydrazine. They were used for three-axis control during coast phases, roll control during J-2 firings, and ullage for the second ignition of the J-2 engine. A surplus S-IVB tank, serial number 212, was converted into the hull for the Skylab, the first American space station. Skylab was launched on a Saturn V on May 14, 1973, but it eventually reentered the atmosphere on July 11, 1979. A second S-IVB, serial number 515, was also converted into a backup Skylab,"
"developed, but all its stages were used on different launch vehicles, now retired as of today. Juno V-B, studied in the same year as Juno V-A, was proposed for lunar and interplanetary missions into space. It was just like the Juno V-A, except the third stage, originally the second stage of a Titan I booster, would be replaced with a Centaur C high-energy third stage. A year after Juno V-B's study, the booster received a new name: the Saturn A-1, which, like the Juno series of rockets was never built in its original planned form, but all its stages were"
"Saturn INT-20 The Saturn INT-20 was a proposed intermediate-payload follow-on from the Apollo Saturn V launch vehicle. A conical-form interstage would be fitted on top of the S-IC stage to support the S-IVB stage, so it could be considered either a retrofitted Saturn IB with a more powerful first stage, or a stubby, cut-down Saturn V without the S-II second stage. Three variants were studied, one with three F-1 engines in the first stage, one with four, and one with five. Without the S-II stage, which made up a large fraction of the mass of the Saturn V, a version"
"with an equipment carrier. These plans were modified to use the S-IVB when Saturn V production ended with just enough boosters for the lunar missions alone. In the meantime several of the Earth-orbit ""checkout"" missions for Apollo had been canceled, leaving a number of Saturn IBs unused. The plans were changed to use the S-IVB stage, used on both rockets, as the primary station structure. A modified S-IVB would be launched into orbit, the second stage carrying a docking module and large solar panels in the area normally carrying the LM. A CSM would then be able to dock with"