Abstract
This study deals with the in-plane motion of a free-floating planar satellite equipped with two thrusters whose force directions are fixed with respect to the satellite. The system's governing equations form non-integrable second-order "nonholonomic" constraints due to the fixed force directions within the satellite. First, this paper shows the general expressions of the system's equations of motion, and shows that its translational and rotational motions can not be controlled independently. Next, by assuming an imaginary thruster controlled by a feedback law, we transform the nonholonomic constraints into holonomic ones. This concept is followed by a strategy to achieve a rotational motion without drift for a satellite system with two fixed thrusters. Afterwards, this paper shows a procedure for precise control of the position and attitude of the system. The validity of the proposed method is verified by numerical simulations. Finally, this paper discusses the special case when the magnitude of the thruster force is taken constant.
| Original language | English |
|---|---|
| Title of host publication | AIAA Guidance, Navigation, and Control Conference and Exhibit |
| Publication status | Published - 2009 |
| Event | AIAA Guidance, Navigation, and Control Conference and Exhibit - Chicago, IL, United States Duration: Aug 10 2009 → Aug 13 2009 |
Other
| Other | AIAA Guidance, Navigation, and Control Conference and Exhibit |
|---|---|
| Country | United States |
| City | Chicago, IL |
| Period | 8/10/09 → 8/13/09 |
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All Science Journal Classification (ASJC) codes
- Aerospace Engineering
- Control and Systems Engineering
- Electrical and Electronic Engineering
Cite this
Position and attitude control of a planar satellite by two thrusters. / Hokamoto, Shinji; Iwase, Masaoki.
AIAA Guidance, Navigation, and Control Conference and Exhibit. 2009. 2009-6183.Research output: Chapter in Book/Report/Conference proceeding › Conference contribution
}
TY - GEN
T1 - Position and attitude control of a planar satellite by two thrusters
AU - Hokamoto, Shinji
AU - Iwase, Masaoki
PY - 2009
Y1 - 2009
N2 - This study deals with the in-plane motion of a free-floating planar satellite equipped with two thrusters whose force directions are fixed with respect to the satellite. The system's governing equations form non-integrable second-order "nonholonomic" constraints due to the fixed force directions within the satellite. First, this paper shows the general expressions of the system's equations of motion, and shows that its translational and rotational motions can not be controlled independently. Next, by assuming an imaginary thruster controlled by a feedback law, we transform the nonholonomic constraints into holonomic ones. This concept is followed by a strategy to achieve a rotational motion without drift for a satellite system with two fixed thrusters. Afterwards, this paper shows a procedure for precise control of the position and attitude of the system. The validity of the proposed method is verified by numerical simulations. Finally, this paper discusses the special case when the magnitude of the thruster force is taken constant.
AB - This study deals with the in-plane motion of a free-floating planar satellite equipped with two thrusters whose force directions are fixed with respect to the satellite. The system's governing equations form non-integrable second-order "nonholonomic" constraints due to the fixed force directions within the satellite. First, this paper shows the general expressions of the system's equations of motion, and shows that its translational and rotational motions can not be controlled independently. Next, by assuming an imaginary thruster controlled by a feedback law, we transform the nonholonomic constraints into holonomic ones. This concept is followed by a strategy to achieve a rotational motion without drift for a satellite system with two fixed thrusters. Afterwards, this paper shows a procedure for precise control of the position and attitude of the system. The validity of the proposed method is verified by numerical simulations. Finally, this paper discusses the special case when the magnitude of the thruster force is taken constant.
UR - http://www.scopus.com/inward/record.url?scp=78049318063&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=78049318063&partnerID=8YFLogxK
M3 - Conference contribution
AN - SCOPUS:78049318063
SN - 9781563479786
BT - AIAA Guidance, Navigation, and Control Conference and Exhibit
ER -