Electrodynamic tether at Jupiter 2. Tour missions after capture

Sanmartín Losada, Juan Ramón; Charro, Mario; Lorenzini, Enrico C.; Garret, Henry B.; Bramanti, Cristina y Bombardelli, Claudio (2007). Electrodynamic tether at Jupiter 2. Tour missions after capture. En: "10th Spacecraft Charging Technology Conference", 18-21 jun, Biarritz.

Descripción

Título: Electrodynamic tether at Jupiter 2. Tour missions after capture
Autor/es:
  • Sanmartín Losada, Juan Ramón
  • Charro, Mario
  • Lorenzini, Enrico C.
  • Garret, Henry B.
  • Bramanti, Cristina
  • Bombardelli, Claudio
Tipo de Documento: Ponencia en Congreso o Jornada (Artículo)
Título del Evento: 10th Spacecraft Charging Technology Conference
Fechas del Evento: 18-21 jun
Lugar del Evento: Biarritz
Título del Libro: 10th Spacecraft Charging Technology Conference
Fecha: 2007
Materias:
Escuela: E.T.S.I. Aeronáuticos (UPM) [antigua denominación]
Departamento: Física Aplicada a la Ingeniería Aeronáutica [hasta 2014]
Licencias Creative Commons: Reconocimiento - Sin obra derivada - No comercial

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Resumen

Three separate scenarios of an electrodynamic tether mission at Jupiter following capture of a spacecraft (SC) into an equatorial, highly elliptical orbit around the planet, with perijove at about 1.5 times the Jovian radius, are discussed. Repeated application of Lorentz drag on the spinning tether, at the perijove vicinity, can progressively lower the apojove. One mission involves the tethered-SC rapidly and frequently visiting Galilean moons; elliptical orbits with apojove down at the Ganymede, Europa, and Io orbits are in 2:5, 4:9, and 1:2 resonances with the respective moons. About 20 slow flybys of Io would take place before the accumulated radiation dose exceeds 3 Mrad (Si) at 10 mm Al shield thickness, with a total duration of 5 months after capture (4 months for lowering the apojove to Io and one month for the flybys). The respective number of flybys for Ganymede would be 10 with a total duration of about 9 months. An alternative mission would have the SC acquire a low circular orbit around Jupiter, below the radiation belts, and manoeuvre to get an optimal altitude, with no major radiation effects, in less than 5 months after capture. In a third mission, repeated thrusting at the apojove vicinity, once down at the Io torus, would raise the perijove itself to the torus to acquire a low circular orbit around Io in about 4 months, for a total of 8 months after capture; this corresponds, however, to over 100 apojove passes with an accumulated dose, of about 8.5 Mrad (Si), that poses a critical issue.

Más información

ID de Registro: 25883
Identificador DC: http://oa.upm.es/25883/
Identificador OAI: oai:oa.upm.es:25883
Depositado por: Biblioteca ETSI Aeronauticos
Depositado el: 12 May 2014 10:03
Ultima Modificación: 22 Sep 2014 11:38
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