Nonlinear Tracking Attitude Control on Time Dependent Trajectories

Date

2015-08-09

Author

Tekinalp, Ozan
Ataş, Ömer

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http://www.space-flight.org/
https://hdl.handle.net/11511/82297

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Nonlinear tracking attitude control of spacecraft on time dependent trajectories Tekinalp, Ozan; Atas, Omer (2015-08-13) The spacecraft attitude control is carried out using the to-go quatemion. A derivative of the to-go quaternion is derived where the desired attitude is a time dependent function. Based on this new attitude formulation, a proper state dependent coefficient matrix expression is obtained. Then the nonlinear tracking attitude control is realized using the state dependent Riccati equation method. The simulation results are given and discussed.
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Citation Formats

O. Tekinalp and Ö. Ataş, “Nonlinear Tracking Attitude Control on Time Dependent Trajectories,” 2015, Accessed: 00, 2021. [Online]. Available: http://www.space-flight.org/.