NONLINEAR TRACKING ATTITUDE CONTROL OF SPACECRAFT ON TIME DEPENDENT TRAJECTORIES

2015-08-13
Tekinalp, Ozan
Gomroki, Mohammad M.
Atas, Omer
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.
Citation Formats
O. Tekinalp, M. M. Gomroki, 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.