Corpo sustentante: diferenças entre revisões
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Um '''corpo sustentante''' é uma [[aeronave]] na qual a configuração do próprio corpo da [[aeronave]] produz [[Sustentação (aerodinâmica)|sustentação]]. Em contraste com um [[asa voadora]], que é uma asa sem [[fuselagem]] convencional, um corpo sustentante é uma fuselagem que gera sustentação sem a forma de uma estrutura fina e plana típica da asa. Considerando que uma asa voadora visa maximizar a eficiência de cruzeiro em velocidades [[Aerodinâmica|subsônicas]], eliminando superfícies não-sustentantes, os corpos sustentantes geralmente minimizam o arrasto e a estrutura de uma asa para voo subsônico, [[Velocidade supersónica|supersônico]] e [[Escoamento hipersônico|hipersônico]], ou, em [[Nave espacial|veículo espacial]], na [[Reentrada atmosférica|reentrada]]. Todos estes regimes de voo colocam desafios para a estabilidade de voo adequado.
== História ==
Em 1921, o aviador pioneiro e projetista de aeronaves [[Vincent Justus Burnelli]] patenteou o conceito simples de uma estruturas em forma de [[aerofólio]] aumentando a capacidade de elevação e de carga da aeronave.<ref>[http://www.aircrash.org/burnelli/chrono1.htm Burnelli's Lifting Bodies A Photographic Chronology ] {{en}}</ref>
Apesar de uma série de contratempos políticos e empresariais, Burnelli continuou a refinar e licenciar seus projetos fazendo uma série de aperfeiçoamentos com o conceito até à sua morte em 1964.<ref>[http://www.mysteriesofcanada.com/Canada/Canada_Car/burnelli_designs.htm Burnelli's Later Designs and the Current Planes That Copied Them] {{en}}</ref><ref>[http://bennun.biz/features/burnelli.html Burnelli Aircraft (The Sunday Telegraph Magazine, 2002)] {{en}}</ref>
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[[Aerospace]]-related lifting body research arose from the idea of [[spacecraft]] [[Atmospheric reentry|re-entering]] the Earth's atmosphere and landing much like a regular [[aircraft]]. Following atmospheric re-entry, the traditional capsule-like spacecraft from the [[Project Mercury|Mercury]], [[Project Gemini|Gemini]] and [[Apollo Program|Apollo]] series had very little control over where they landed. A steerable spacecraft with wings could significantly extend its landing envelope. However, the vehicle's wings would have to be designed to withstand the dynamic and thermal stresses of both re-entry and hypersonic flight. A proposed solution eliminated wings altogether: Design the fuselage body itself to produce lift. The [[Space Shuttle]] combines some of the proven lifting body principles{{Fact|date=January 2009}} with the [[delta wing]] concept.
[[NASA]]'s refinements of the lifting body concept began in 1962 with [[Dale Reed]] of [[NASA]]'s [[Dryden Flight Research Center]]. The first full-size model to come out of Reed's program was the [[NASA M2-F1]], an unpowered craft made of wood. Initial tests were performed by towing the '''M2-F1''' along a California dry lakebed at present-day Edwards Air Force Base, behind a [[Hot rod|modified]] [[Pontiac Catalina]] <ref>[http://www.classicalpontiac.com/articles/nasa.html Classical Pontiac and NASA]</ref>. Later the craft was towed behind a [[C-47 Skytrain|C-47]] and released. Since the M2-F1 was a [[glider aircraft|glider]], a small [[rocket motor]] was added in order to extend the landing envelope. The M2-F1 was soon nicknamed the "Flying Bathtub".
In 1963, NASA began programs with heavier rocket powered lifting body vehicles to be air launched from under the starboard wing of a NB-52B, a derivative of the [[B-52 Stratofortress|B-52]] jet bomber. The first flights started in 1966. Of the Dryden lifting bodies, all but the unpowered [[NASA M2-F1]] used an [[XLR-11]] rocket engine as was used on the famous [[Bell X-1]].{{Fact|date=January 2009}} A follow-on design designated the [[Northrop HL-10]] was developed at NASA [[Langley Research Center]]. The [[Martin-Marietta X-24|X-24A and X-24B]] lifting body designs were based on the M2 concept originated in 1957 by [[Dr. Alfred J. Eggers|Alfred Eggers]] of NASA [[Ames Aeronautical Laboratory]]. The M-2 competed in the design of the Space Shuttle.{{Fact|date=January 2009}}
A major instability problem with these designs was discovered during the course of flight testing. It was determined that induced ''[[flow separation|air flow separation]]'', in which the air stream would become very turbulent, would cause loss of control and lift{{Fact|date=January 2009}}. The HL-10 attempted to solve part of this problem by angling the [[Port (nautical)|port]] and [[starboard]] [[vertical stabilizer]]s outward and enlarging the center one. Air flow separation caused the crash of the [[Northrop M2-F2]] lifting body. The successor [[Northrop M2-F3]] added a third (central) vertical stabilizer to the aerodynamically flawed '''M2-F2''' design in an attempt to correct the flow separation instabilities.
The [[X-38]] program, developed under leadership of NASA Johnson Space Center, built an incremental series of flight demonstrators pursuant to the proposed Crew Return Vehicle (CRV) for the International Space Station. The X-38 was a lifting body based on the outer mold line of the [[Martin-Marietta X-24|X-24]].
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{{em tradução|:en:Lifting body}}
== Referências ==
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[[Categoria:Aviões]]
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