Abstract
This research proposes a relative position and attitude control method without reaction wheels, using magnetic force with multi-dipole for formation-flying spacecraft. This technology can be widely applied to re-configurable space structures that architect large structure, such like restructuring themselves by assembling basic structural units. One remarkable benefit is that this control method doesn't limit mission term because it never requires any types of fuel to drive RW for attitude control or unloading. So we focused on current control of dipoles which produce strong nonlinear magnetic forces and suggested a way of linearization of a nonlinear system for control by using reference controllable system. Also feasibility of this method and controllability were investigated, then the series of position and attitude control simulation were shown.
| Original language | English |
|---|---|
| Title of host publication | AIAA Guidance, Navigation, and Control (GNC) Conference |
| Publication status | Published - 2013 |
| Event | AIAA Guidance, Navigation, and Control (GNC) Conference - Boston, MA Duration: 2013 Aug 19 → 2013 Aug 22 |
Other
| Other | AIAA Guidance, Navigation, and Control (GNC) Conference |
|---|---|
| City | Boston, MA |
| Period | 13/8/19 → 13/8/22 |
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ASJC Scopus subject areas
- Aerospace Engineering
- Control and Systems Engineering
- Electrical and Electronic Engineering
Cite this
Position and attitude control of formation flying satellites for restructuring their configurations by electromagnetic forces at the docking phase. / Torisaka, Ayako; Ozawa, Satoru; Yamakawa, Hiroshi; Kobayashi, Nobuyuki.
AIAA Guidance, Navigation, and Control (GNC) Conference. 2013.Research output: Chapter in Book/Report/Conference proceeding › Conference contribution
}
TY - GEN
T1 - Position and attitude control of formation flying satellites for restructuring their configurations by electromagnetic forces at the docking phase
AU - Torisaka, Ayako
AU - Ozawa, Satoru
AU - Yamakawa, Hiroshi
AU - Kobayashi, Nobuyuki
PY - 2013
Y1 - 2013
N2 - This research proposes a relative position and attitude control method without reaction wheels, using magnetic force with multi-dipole for formation-flying spacecraft. This technology can be widely applied to re-configurable space structures that architect large structure, such like restructuring themselves by assembling basic structural units. One remarkable benefit is that this control method doesn't limit mission term because it never requires any types of fuel to drive RW for attitude control or unloading. So we focused on current control of dipoles which produce strong nonlinear magnetic forces and suggested a way of linearization of a nonlinear system for control by using reference controllable system. Also feasibility of this method and controllability were investigated, then the series of position and attitude control simulation were shown.
AB - This research proposes a relative position and attitude control method without reaction wheels, using magnetic force with multi-dipole for formation-flying spacecraft. This technology can be widely applied to re-configurable space structures that architect large structure, such like restructuring themselves by assembling basic structural units. One remarkable benefit is that this control method doesn't limit mission term because it never requires any types of fuel to drive RW for attitude control or unloading. So we focused on current control of dipoles which produce strong nonlinear magnetic forces and suggested a way of linearization of a nonlinear system for control by using reference controllable system. Also feasibility of this method and controllability were investigated, then the series of position and attitude control simulation were shown.
UR - http://www.scopus.com/inward/record.url?scp=84883738008&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=84883738008&partnerID=8YFLogxK
M3 - Conference contribution
AN - SCOPUS:84883738008
SN - 9781624102240
BT - AIAA Guidance, Navigation, and Control (GNC) Conference
ER -