Space Shuttle external tank WikipediaExternal fuel tank redirects here. For expendable tanks carried by aircraft, see Drop tank. The ET from STS 1. Pl-2303 Usb To Serial Driver Windows 7. The scorch mark near the front end of the tank is from the SRB separation motors. Booster separation motorA Space Shuttle External Tank ET was the component of the Space Shuttlelaunch vehicle that contained the liquid hydrogenfuel and liquid oxygenoxidizer. H2 Weight Loss' title='H2 Weight Loss' />
During lift off and ascent it supplied the fuel and oxidizer under pressure to the three Space Shuttle Main Engines SSME in the orbiter. The ET was jettisoned just over 1. MECO Main Engine Cut Off, where the SSMEs were shut down, and re entered the Earths atmosphere. Unlike the Solid Rocket Boosters, external tanks were not re used. They broke up before impact in the Indian Ocean or Pacific Ocean in the case of direct insertion launch trajectories, away from shipping lanes and were not recovered. OvervieweditThe External Tank was painted white for the first two Space Shuttle launches. From STS 3 on, it was left unpainted. Glucose tolerance factor chromium, more commonly called chromium GTF, is a mineral that is frequently used in bodybuilding, athletic and weightloss. The ET was the largest element of the space shuttle, and when loaded, it was also the heaviest. It consisted of three major components the forward liquid oxygen LOX tankan unpressurized intertank that contains most of the electrical componentsthe aft liquid hydrogen LH2 tank this was the largest part, but it was relatively light, due to liquid hydrogens very low density. The ET was the backbone of the shuttle during launch, providing structural support for attachment with the Space Shuttle Solid Rocket Boosters SRBs and orbiter. I/51vIi9PqHTL.01_SL500_.jpg' alt='H2 Weight Loss' title='H2 Weight Loss' />The all new 2017 Alkaviva Vesta H2 Water Ionizer is quite simply the best water Ionizer for sale in world today. No other water Ionizer we have ever tested comes. The tank was connected to each SRB at one forward attachment point using a crossbeam through the intertank and one aft bracket, and it was connected to the orbiter at one forward attachment bipod and two aft bipods. In the aft attachment area, there were also umbilicals that carried fluids, gases, electrical signals and electrical power between the tank and the orbiter. Electrical signals and controls between the orbiter and the two solid rocket boosters were also routed through those umbilicals. Although the external tanks were always discarded, it could have been possible to re use them in orbit. Plans for re use ranged from incorporation into a space station as extra living or research space, as rocket fuel tanks for interplanetary missions e. Mars, to raw materials for orbiting factories. Another concept was to use the ET as a cargo carrier for bulky payloads. One proposal was for the primary mirror of a 7 meter aperture telescope to be carried with the tank. Another concept was the Aft Cargo Carrier ACC. VersionseditOver the years, NASA worked to reduce the weight of the ET to increase overall efficiency. For each pound of weight reduction, the cargo carrying capability of the shuttle spacecraft was increased almost one pound. Standard Weight TankeditThe original ET is informally known as the Standard Weight Tank SWT and was fabricated from 2. The first two, used for STS 1 and STS 2, were painted white to protect the tanks from ultraviolet light during the extended time that the shuttle spends on the launch pad prior to launch. Because this did not turn out to be a problem, Lockheed Martin at that time, Martin Marietta reduced weight by leaving the rust colored spray on insulation unpainted beginning with STS 3, saving approximately 2. After STS 4, several hundred pounds were eliminated by deleting the anti geyser line. This line paralleled the oxygen feed line, providing a circulation path for liquid oxygen. This reduces accumulation of gaseous oxygen in the feed line during prelaunch tanking loading of the LOX. H2 Weight Loss' title='H2 Weight Loss' />After propellant loading data from ground tests and the first few space shuttle missions were assessed, the anti geyser line was removed for subsequent missions. The total length and diameter of the ET remain unchanged. The last SWT, flown on STS 7, weighed approximately 3. Lightweight TankeditBeginning with the STS 6 mission, a lightweight ET LWT, was introduced. This tank was used for the majority of the Shuttle flights, and was last used on the ill fated Space Shuttle Columbia disaster STS 1. Although tanks vary slightly in weight, each weighed approximately 3. The weight reduction from the SWT was accomplished by eliminating portions of stringers structural stiffeners running the length of the hydrogen tank, using fewer stiffener rings and by modifying major frames in the hydrogen tank. Also, significant portions of the tank were milled differently so as to reduce thickness, and the weight of the ETs aft solid rocket booster attachments was reduced by using a stronger, yet lighter and less expensive titanium alloy. Super Lightweight TankeditThe Super Lightweight Tank SLWT was first flown in 1. STS 9. 1 and was used for all subsequent missions with two exceptions STS 9. STS 1. 07. 8 The SLWT had basically the same design as the LWT except that it used an aluminium lithium alloy Al 2. This alloy provided a significant reduction in tank weight 3,1. LWT. Manufacture also included friction stir welding technology. Although all ETs produced after the introduction of the SLWT were of this configuration, one LWT remained in inventory to be used if requested until the end of the shuttle era. The SLWT provided 5. International Space Station. The reduction in weight allowed the Orbiter to carry more payload to the highly inclined orbit of the ISS. The Pegasus barge carrying ET 1. Port Canaveral. Technical specificationseditSLWT Specifications8Length 1. Diameter 2. 7. 6 ft 8. Empty Weight 5. 8,5. Gross Liftoff Weight 1,6. LOX tank. Length 5. Diameter 2. 7. 6 ft 8. Volume at 2. 2 psig 1. US gal 5. 53,3. 58 lLOX mass at 2. Freeware Cpu Temperature Utility here. Operation Pressure 3. Pa gauge absoluteIntertank. Length 2. 2. 6 ft 6. Diameter 2. 7. 6 ft 8. LH2 tank. Length 9. Diameter 2. 7. 6 ft 8. Volume at 2. 9. 3 psig 5. US gal 1,4. 97,4. LH2 mass at 2. 9. Operation Pressure 3. Pa absoluteOperation Temperature 4. F 2. 52. 8 C9ContractoreditThe contractor for the external tank was Lockheed Martin previously Martin Marietta, New Orleans, Louisiana. The tank was manufactured at the Michoud Assembly Facility, New Orleans, and was transported to Kennedy Space Center by barge. Ac97 Audio Drivers For Windows 7 on this page. ComponentseditThe ET has three primary structures an LOX tank, an intertank, and an LH2 tank. Both tanks are constructed of aluminium alloy skins with support or stability frames as required. The intertank aluminium structure utilizes skin stringers with stabilizing frames. The primary aluminium materials used for all three structures are 2. AL 2. 19. 5 is an Al Li alloy designed by Lockheed Martin and Reynolds for storage of cryogenics and used for the SLW version of the ET earlier versions used Al 2. Al 2. 09. 0 is a commercially available Al Li alloy. Anatomy of the External Tank. Liquid oxygen tankeditThe LOX tank is located at the top of the ET and has an ogive shape to reduce aerodynamic drag and aerothermodynamic heating. The ogive nose section is capped by a flat removable cover plate and a nose cone. The nose cone consists of a removable conical assembly that serves as an aerodynamic fairing for the propulsion and electrical system components. The forward most element of the nose cone functions as a cast aluminium lightning rod. The LOX tank volume is 1. 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