The paper investigates the dynamic behavior of a spacecraft when a single magnetic torque-rod is used for achieving a pure spin condition by means of the so-called Y-dot control law. Global asymptotic convergence to a pure spin condition is proven on analytical grounds when the dipole moment is proportional to the rate of variation of the component of the magnetic field along the desired spin axis. Convergence of the spin axis towards the orbit normal is then explained by estimating the average magnetic control torque over one orbit. The validity of the analytical results, based on some simplifying assumptions and approximations, is finally investigated by means of numerical simulation for a fully non-linear attitude dynamic model, featuring a tilted dipole model for Earth׳s magnetic field. The analysis aims to support, in the framework of a sound mathematical basis, the development of effective control laws in realistic mission scenarios. Results are presented and discussed for relevant test cases.
Spacecraft dynamics under the action of Y-dot magnetic control law / Zavoli, Alessandro; Giulietti, Fabrizio; Avanzini, Giulio; DE MATTEIS, Guido. - In: ACTA ASTRONAUTICA. - ISSN 0094-5765. - STAMPA. - 122:(2016), pp. 146-158. [10.1016/j.actaastro.2016.01.024]
Spacecraft dynamics under the action of Y-dot magnetic control law
ZAVOLI, ALESSANDRO
;DE MATTEIS, GUIDO
2016
Abstract
The paper investigates the dynamic behavior of a spacecraft when a single magnetic torque-rod is used for achieving a pure spin condition by means of the so-called Y-dot control law. Global asymptotic convergence to a pure spin condition is proven on analytical grounds when the dipole moment is proportional to the rate of variation of the component of the magnetic field along the desired spin axis. Convergence of the spin axis towards the orbit normal is then explained by estimating the average magnetic control torque over one orbit. The validity of the analytical results, based on some simplifying assumptions and approximations, is finally investigated by means of numerical simulation for a fully non-linear attitude dynamic model, featuring a tilted dipole model for Earth׳s magnetic field. The analysis aims to support, in the framework of a sound mathematical basis, the development of effective control laws in realistic mission scenarios. Results are presented and discussed for relevant test cases.File | Dimensione | Formato | |
---|---|---|---|
Zavoli_preprint_spacecraft-dynamics_2016.pdf
accesso aperto
Note: Articolo in pre-print
Tipologia:
Documento in Pre-print (manoscritto inviato all'editore, precedente alla peer review)
Licenza:
Tutti i diritti riservati (All rights reserved)
Dimensione
5.12 MB
Formato
Adobe PDF
|
5.12 MB | Adobe PDF | |
Zavoli_Spacecraft-dynamics_2016.pdf
solo gestori archivio
Tipologia:
Versione editoriale (versione pubblicata con il layout dell'editore)
Licenza:
Tutti i diritti riservati (All rights reserved)
Dimensione
1.63 MB
Formato
Adobe PDF
|
1.63 MB | Adobe PDF | Contatta l'autore |
I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.