Information AboutLiquid Rocket |
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HISTORY , bundled against the cold New England weather of March 16 , 1926 , holds the launching frame of his most notable invention — the first liquid rocket.]] The idea of liquid fuel rocket as understood in the modern context first appears in the book Исследование мировых пространств реактивными приборами (Romanisation: Issledovanie mirovh prostranst {Link without Title} v) (The Exploration of Cosmic Space by Means of Reaction Devices), by Konstantin Eduardovitch Tsiolkovsky . This seminal treatise on astronautics was published in 1903. The only known claim to liquid propellant rocket engine experiments in the nineteenth century was made by Pedro Paulet , a Peruvian scientist. 1 However, he did not immediately publish his work. In 1927 he wrote a letter to a newspaper in Lima , claiming he had experimented with a liquid rocket engine while he was a student in Paris three decades earlier. Historians of early rocketry experiments, among them Max Valier and Willy Ley , have given differing amounts of credence to Paulet's report. Paulet described laboratory tests of liquid rocket engines, but did not claim to have flown a liquid rocket. The first flight of a vehicle powered by a liquid-rocket took place on March 16 , 1926 at Auburn, Massachusetts , when American professor Robert H. Goddard launched a rocket which used Liquid Oxygen and gasoline as propellants. 2 The rocket, which was dubbed "Nell", rose just 41 feet during a 2.5-second flight that ended in a cabbage field, but it was an important demonstration that liquid-fueled rockets were possible. ADVANTAGES OF LIQUID ROCKETS Unlike gases, a typical liquid propellant has a density similar to water, approximately 0.7-1.4g/cm3 (except Liquid Hydrogen which has a very much lower density), while requiring only relatively modest pressuristation to prevent vapourisation. This combination of density and low pressure permits very lightweight tankage; approximately 1% of the contents for dense propellants and around 10% for liquid hydrogen (due to its low density and the mass of the required insulation). For injection into the combustion chamber the propellant pressure needs to be greater than the chamber pressure at the injectors; this is can be achieved with a pump. Suitable pumps usually use Turbopumps due to their high power and lightweight, although reciprocating pumps have been employed in the past. Turbopumps are usually extremely lightweight and can give excellent performance. Alternatively, a heavy tank can be used, and the pump foregone; but the delta-v that the stage can achieve is much lower. DISADVANTAGES OF LIQUID ROCKETS Liquid propellants can cause a number of issues:
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