In this thesis, attitude control of small satellites with dissimilar actuator is
studied and the effects of control allocation methods on maneuvering are examined
in detail. Magnetorquers and reaction wheels are considered as the actuators of a
modeled remote sensing -nadir pointing- small satellite. Matlab® / Simulink
simulation models are developed to model the satellite dynamics and the actuators on
the satellite. The simulations are based on conceptual RASAT satellite, and, for
verification, orbit data is taken from BILSAT satellite that is operated by TUBITAK
Space Research Institute.
Basic satellite control modes are developed and tested to obtain nominal
control. Actuator failures are analyzed for different possible cases.
A control allocation method called Blended Inverse that was originally
proposed for steering CMGs is applied to select the actuators to avoid actuator
saturation and singularity transition. The performance of traditional pseudo inverse
method is compared with the blended inverse method and simulation results are
given and discussed. The superiority of blended inverse over pseudo inverse is
demonstrated.
| Identifer | oai:union.ndltd.org:METU/oai:etd.lib.metu.edu.tr:http://etd.lib.metu.edu.tr/upload/12609038/index.pdf |
| Date | 01 November 2007 |
| Creators | Kahraman, Ozgur |
| Contributors | Tekinalp, Ozan |
| Publisher | METU |
| Source Sets | Middle East Technical Univ. |
| Language | English |
| Detected Language | English |
| Type | M.S. Thesis |
| Format | text/pdf |
| Rights | To liberate the content for public access |
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