Orbital control of satellite systems using nonholonomic control theory

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Abstract

This study deals with orbital control of a rigid dumbbell-type satellite system. While most of the previous works for orbital transfer aim at changing just one parameter of the orbital element or the orbital energy, in this study the system is transferred by using its inner force into a prescribed orbit defined as a set of orbital elements: semilatus rectum, eccentricity, and argument of pericenter. By applying nonlinear control theories, it is shown that the satellite system is controllable except its pericenter and its apocenter in the elliptic orbit. Then, this paper transforms the nonlinear governing equations into a canonical system, called 'a chained system', and demonstrates that a specified orbit is accomplished by appropriately shaped time histories of control inputs.

Original languageEnglish
Title of host publicationAstrodynamics 2005 - Advances in the Astronautical Sciences - Proceedings of the AAS/AIAA Astrodynamics Conference
Pages1533-1544
Number of pages12
Volume123 II
Publication statusPublished - 2006
EventAstrodynamics 2005 - Advances in the Astronautical Sciences - Proceedings of the AAS/AIAA Astrodynamics Conference - South Lake Tahoe, CA, United States
Duration: Aug 7 2005Aug 11 2005

Other

OtherAstrodynamics 2005 - Advances in the Astronautical Sciences - Proceedings of the AAS/AIAA Astrodynamics Conference
CountryUnited States
CitySouth Lake Tahoe, CA
Period8/7/058/11/05

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All Science Journal Classification (ASJC) codes

  • Aerospace Engineering

Cite this

Hokamoto, S. (2006). Orbital control of satellite systems using nonholonomic control theory. In Astrodynamics 2005 - Advances in the Astronautical Sciences - Proceedings of the AAS/AIAA Astrodynamics Conference (Vol. 123 II, pp. 1533-1544)