Control laws for orbital parameters of rigid satellite system considering nonholonomic constraint

Koki Fujita, Shinji Hokamoto

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

This study deals with orbital control of a rigid coplanar dumbbell-type satellite system. While most of the previous work for orbital transfer aim at changing just one parameter of the orbital elements, by applying a nonlinear method, this study proposes two control laws to change an orbit into a prescribed one defined by its orbital elements: semi-major axis (equivalent to semilatus rectum), eccentricity and argument of pericenter. First controller is developed from a two-step approach combining a solution for a chained formed system and numerical modification based on motion planning. Another is a feedback controller, which can compensate model uncertainty or disturbance. These two controllers can be combined to a complementary control technique. The effectiveness of the proposed control laws are demonstrated through a series of numerical simulations.

Original languageEnglish
Title of host publicationCollection of Technical Papers - AIAA Guidance, Navigation, and Control Conference 2007
Pages5073-5085
Number of pages13
Publication statusPublished - Dec 24 2007
EventAIAA Guidance, Navigation, and Control Conference 2007 - Hilton Head, SC, United States
Duration: Aug 20 2007Aug 23 2007

Publication series

NameCollection of Technical Papers - AIAA Guidance, Navigation, and Control Conference 2007
Volume5

Other

OtherAIAA Guidance, Navigation, and Control Conference 2007
CountryUnited States
CityHilton Head, SC
Period8/20/078/23/07

Fingerprint

Satellites
Controllers
Orbital transfer
Motion planning
Orbits
Feedback
Computer simulation
Uncertainty

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Control and Systems Engineering
  • Electrical and Electronic Engineering

Cite this

Fujita, K., & Hokamoto, S. (2007). Control laws for orbital parameters of rigid satellite system considering nonholonomic constraint. In Collection of Technical Papers - AIAA Guidance, Navigation, and Control Conference 2007 (pp. 5073-5085). (Collection of Technical Papers - AIAA Guidance, Navigation, and Control Conference 2007; Vol. 5).

Control laws for orbital parameters of rigid satellite system considering nonholonomic constraint. / Fujita, Koki; Hokamoto, Shinji.

Collection of Technical Papers - AIAA Guidance, Navigation, and Control Conference 2007. 2007. p. 5073-5085 (Collection of Technical Papers - AIAA Guidance, Navigation, and Control Conference 2007; Vol. 5).

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Fujita, K & Hokamoto, S 2007, Control laws for orbital parameters of rigid satellite system considering nonholonomic constraint. in Collection of Technical Papers - AIAA Guidance, Navigation, and Control Conference 2007. Collection of Technical Papers - AIAA Guidance, Navigation, and Control Conference 2007, vol. 5, pp. 5073-5085, AIAA Guidance, Navigation, and Control Conference 2007, Hilton Head, SC, United States, 8/20/07.
Fujita K, Hokamoto S. Control laws for orbital parameters of rigid satellite system considering nonholonomic constraint. In Collection of Technical Papers - AIAA Guidance, Navigation, and Control Conference 2007. 2007. p. 5073-5085. (Collection of Technical Papers - AIAA Guidance, Navigation, and Control Conference 2007).
Fujita, Koki ; Hokamoto, Shinji. / Control laws for orbital parameters of rigid satellite system considering nonholonomic constraint. Collection of Technical Papers - AIAA Guidance, Navigation, and Control Conference 2007. 2007. pp. 5073-5085 (Collection of Technical Papers - AIAA Guidance, Navigation, and Control Conference 2007).
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