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Saturn V-A
Saturn V-A was a proposed American orbital launch vehicle. It was studied by Marshall Space Flight Center in 1968. the Saturn V-A was identical to the Saturn INT-20, except it consisted of an ordinary S-IC first stage and S-IVB The S-IVB (pronounced "S-four-B") was the third stage on the Saturn V and second stage on the Saturn IB launch vehicles. Built by the Douglas Aircraft Company, it had one J-2 rocket engine. For lunar missions it was fired twice: first for Earth ... second stage. For deep-space missions, a Centaur third stage could also have been used. Details Details Saturn V-A of Saturn V-A: Gross mass: 2,478,120 kg (5,463,310 lb). Payload: 60,000 kg (132,000 lb). Height: 72.00 m (236.00 ft). Diameter: 10.06 m (33.00 ft). Thrust: 33,737.90 kN (7,584,582 lbf). Apogee: 185 km (114 mi). References {{Saturns Saturn (rocket family) ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Marshall Space Flight Center
The George C. Marshall Space Flight Center (MSFC), located in Redstone Arsenal, Alabama (Huntsville postal address), is the U.S. government's civilian rocketry and spacecraft propulsion research center. As the largest NASA center, MSFC's first mission was developing the Saturn launch vehicles for the Apollo program. Marshall has been the lead center for the Space Shuttle main propulsion and external tank; payloads and related crew training; International Space Station (ISS) design and assembly; computers, networks, and information management; and the Space Launch System (SLS). Located on the Redstone Arsenal near Huntsville, MSFC is named in honor of General of the Army George C. Marshall. The center contains the Huntsville Operations Support Center (HOSC), also known as the International Space Station Payload Operations Center. This facility supports ISS launch, payload, and experiment activities at the Kennedy Space Center. The HOSC also monitors rocket launches from Cape ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
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. Performance Without the S-II stage, which made up a large fraction of the mass of the Saturn V, a version of the INT-20 using an unmodified five-engine version of the S-IC booster would be greatly overpowered and accelerate substantially faster than the Saturn V. This would create excessive aerodynamic stress in the low atmosphere. Several solutions to this problem were considered. Using the original five-engine S-IC would require three engines to be shut down 88 seconds after launch, with the remainder of the first-stage ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
S-IC
The S-IC (pronounced S-one-C) was the first stage of the American Saturn V rocket. The S-IC stage was manufactured by the Boeing Company. Like the first stages of most rockets, most of its mass of more than at launch was propellant, in this case RP-1 rocket fuel and liquid oxygen (LOX) oxidizer. It was tall and in diameter, and provided of thrust to get the rocket through the first of ascent. The stage had five F-1 engines in a quincunx arrangement. The center engine was fixed in position, while the four outer engines could be hydraulically gimballed to control the rocket. Manufacturing The Boeing Co. was awarded the contract to manufacture the S-IC on December 15, 1961. By this time the general design of the stage had been decided on by the engineers at the Marshall Space Flight Center (MSFC). The main place of manufacture was the Michoud Assembly Facility, New Orleans. Wind tunnel testing took place in Seattle and the machining of the tools needed to build the stages at W ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
S-IVB
The S-IVB (pronounced "S-four-B") was the third stage on the Saturn V and second stage on the Saturn IB launch vehicles. Built by the Douglas Aircraft Company, it had one J-2 (rocket engine), J-2 rocket engine. For lunar missions it was fired twice: first for Earth orbit insertion after second stage cutoff, and then for translunar injection (TLI). History 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 as the S-IVB – liquid hydrogen and liquid oxygen. It was also originally meant to be the fourth stage of a planned rocket called the Saturn C-4, C-4, hence the name S-IV. Eleven companies submitted proposals for being the lead contractor on the stage by the deadline of 29 February 1960. NASA administrator T. Keith Glennan decided on 19 April that Douglas Aircraft Company would be awarded the contract. Convair had come a close second but G ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Centaur (rocket Stage)
The Centaur is a family of rocket propelled upper stages produced by U.S. launch service provider United Launch Alliance, with one main active version and one version under development. The diameter Common Centaur/Centaur III flies as the upper stage of the Atlas V launch vehicle, and the diameter Centaur V is being developed as the upper stage of ULA's new Vulcan rocket. Centaur was the first rocket stage to use liquid hydrogen (LH2) and liquid oxygen (LOX) propellants, a high-energy combination that is ideal for upper stages but has significant handling difficulties. Characteristics Common Centaur is built around stainless steel pressure stabilized balloon propellant tanks with thick walls. It can lift payloads of up to . The thin walls minimize the mass of the tanks, maximizing the stage's overall performance. A common bulkhead separates the LOX and LH2 tanks, further reducing the tank mass. It is made of two stainless steel skins separated by a fiberglass honeycomb. T ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
