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Finite Horizon Optimal Nonlinear Spacecraft Attitude Control

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Abstract

This research is devoted to present spacecraft attitude control via a finite-horizon nonlinear optimal control technique. The spacecraft kinematics are represented using the modified Rodrigues parameters, which possess singularities for eigenaxis rotations greater than 180 degree. The proposed technique is based on State Dependent Riccati Equation (SDRE). In this technique, the differential Riccati equation is converted to a linear Lyapunov differential equation. This technique can be applied for finite-horizon nonlinear regulation and tracking problems. The proposed technique is effective for a wide range of operating points. Simulation results are given to illustrate the effectiveness of the finite horizon technique.

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Authors and Affiliations

  1. Military Technical College, Cairo, Egypt

    Ahmed Khamis

  2. University of Nevada, Las Vegas, USA

    Dawid Zydek

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  1. Ahmed Khamis
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  2. Dawid Zydek
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Correspondence to Ahmed Khamis.

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Khamis, A., Zydek, D. Finite Horizon Optimal Nonlinear Spacecraft Attitude Control. J Astronaut Sci 67, 1002–1020 (2020). https://doi.org/10.1007/s40295-019-00189-w

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