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@MastersThesis{Borges:2009:EsExLa,
               author = "Borges, Marcos de Melo",
                title = "Estudo experimental do lan{\c{c}}ador hipers{\^o}nico de massa",
               school = "Instituto Nacional de Pesquisas Espaciais (INPE)",
                 year = "2009",
              address = "S{\~a}o Jos{\'e} dos Campos",
                month = "2009-03-31",
             keywords = "hipers{\^o}nica, RAM accelerator, two stage light gas gun, 
                         compressor a pist{\~a}o livre, hypersonic, RAM accelerator, two 
                         stage gas gun, free piston compressor.",
             abstract = "Os avan{\c{c}}os na tecnologia aeroespacial tornaram 
                         imprescind{\'{\i}}veis ensaios em laborat{\'o}rios de 
                         ve{\'{\i}}culos hipers{\^o}nicos. Em conseq{\"u}{\^e}ncia 
                         houve a necessidade de desenvolver dispositivos capazes de gerar 
                         tais condi{\c{c}}{\~o}es. Um dos m{\'e}todos utilizados para 
                         simular essas condi{\c{c}}{\~o}es {\'e} o Lan{\c{c}}ador 
                         Hipers{\^o}nico de Massa (LHM), que vem merecendo 
                         consider{\'a}vel interesse, tanto no campo experimental quanto no 
                         te{\'o}rico. Este trabalho consiste da montagem e estudo 
                         experimental deste dispositivo. O Lan{\c{c}}ador Hipers{\^o}nico 
                         de Massa {\'e} dividido em duas partes, a se{\c{c}}{\~a}o de 
                         compress{\~a}o e a se{\c{c}}{\~a}o de acelera{\c{c}}{\~a}o. A 
                         se{\c{c}}{\~a}o de compress{\~a}o {\'e} composta de um 
                         compressor a pist{\~a}o livre, do qual s{\~a}o descritos 
                         resumidamente neste trabalho detalhes t{\'e}cnicos e operacionais 
                         de cada componente do sistema. Os par{\^a}metros: massa do 
                         pist{\~a}o, comprimento do tubo de compress{\~a}o, press{\~a}o 
                         no tanque de alta press{\~a}o e press{\~a}o no interior do tubo 
                         de compress{\~a}o s{\~a}o analisados experimentalmente e 
                         comparados a um modelo num{\'e}rico b{\'a}sico. Na 
                         se{\c{c}}{\~a}o de acelera{\c{c}}{\~a}o s{\~a}o descritos 
                         resumidamente detalhes t{\'e}cnicos e operacionais de cada 
                         componente do sistema. {\'E} descrito o conceito de velocidade de 
                         detona{\c{c}}{\~a}o de Chapman Jouguet da mistura 
                         energ{\'e}tica verificando sua influ{\^e}ncia na 
                         acelera{\c{c}}{\~a}o do modelo atrav{\'e}s dos regimes de 
                         propuls{\~a}o. S{\~a}o apresentados dados experimentais da 
                         velocidade do modelo antes e ap{\'o}s penetrar no est{\'a}gio da 
                         se{\c{c}}{\~a}o de acelera{\c{c}}{\~a}o que contem em seu 
                         interior uma mistura propelente. ABSTRACT: Recent developments in 
                         aerospace technology have made ground tests of hypersonic vehicles 
                         mandatory. As a consequence, the need to develop facilities 
                         capable of producing hypersonic flight conditions is essential. 
                         One of the methods employed to simulate such conditions is the 
                         Hypersonic Mass Launcher (LHM), which has attracted considerable 
                         attention, both in experimental and in theoretical fields. This 
                         work discusses both the assembly and the experimental study of 
                         this facility. The LHM comprises two main sessions, one for gas 
                         compression and the other for model acceleration. The compression 
                         session is composed by one free piston compressor, whose technical 
                         and operational details of each component of the system are 
                         described. Piston mass, compression tube length, pressure at the 
                         high-pressure tank and pressure inside the compression tube have 
                         been analyzed experimentaly and compared to a numerical model. In 
                         the acceleration tube, technical and operational details of each 
                         component of the system are described. The concept of the 
                         Chapman-Jouguet detonation velocity of an energetic mixture, as 
                         well the investigaton of its influence on the model acceleration 
                         across the propulsion regime are presented. Velocity data, before 
                         and after the model penetration into the acceleration tube, 
                         containning an energetic gas mixture inside, are also presented 
                         and discussed.",
            committee = "Netto, Dem{\'e}trio Bastos (presidente) and Minucci, Marco 
                         Ant{\^o}nio Sala (orientador) and Toledo, Antonio Osny de and 
                         Filho, Jos{\'e} Bezerra Pessoa",
           copyholder = "SID/SCD",
         englishtitle = "Experimental study of the hypersonic mass launcher",
             language = "pt",
                pages = "87",
                  ibi = "8JMKD3MGP8W/352R46H",
                  url = "http://urlib.net/rep/8JMKD3MGP8W/352R46H",
           targetfile = "publicacao.pdf",
        urlaccessdate = "2020, Jan. 18"
}


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