Small-time local controllability of spacecraft attitude using control moment gyros

Haichao Gui ^[1] ; Lei Jin ^[1] ; Shijie Xu ^[1]
1. [1] Beihang University
  
  Beihang University
  
  China
Localización: Automatica: A journal of IFAC the International Federation of Automatic Control, ISSN 0005-1098, Vol. 53, 2015, págs. 141-148
Idioma: inglés
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Resumen
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  Nonlinear controllability theory is utilized to investigate the small-time local controllability (STLC) of the combined dynamics of a spacecraft with control moment gyros (CMGs). Specifically speaking, with three or more independent-type CMGs, the dynamics are STLC from, and hence can be stabilized via time-invariant piecewise continuous feedback laws to, the equilibrium as long as the CMGs never reach certain definite singularities and semidefinite singularities at the equilibrium. These results are then applied to a spacecraft carrying four pyramid-type CMGs and further extended to a spacecraft using roof-type CMGs, in addition to the special case of two CMGs.