Nonlinear tracking attitude control of spacecraft on time dependent trajectories

Date

2015-08-13

Author

Tekinalp, Ozan
Atas, Omer

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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.

Subject Keywords

Spacecraft attitude, Riccati equation method

URI

https://hdl.handle.net/11511/53221

Conference Name

AAS/AIAA Astrodynamics Specialist Conference

Collections

Department of Aerospace Engineering, Conference / Seminar

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Citation Formats

O. Tekinalp and O. Atas, “Nonlinear tracking attitude control of spacecraft on time dependent trajectories,” Vail, CO, 2015, vol. 156, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/53221.