Finite Horizon Optimal Nonlinear Spacecraft Attitude Control

Document Type

Article

Publication Date

8-22-2019

Publication Title

The Journal of the Astronautical Sciences

Volume

67

First page number:

1002

Last page number:

1020

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.

Keywords

SDRE; Nonlinear Control; Spacecraft Attitude Control

Disciplines

Astrophysics and Astronomy | Physical Sciences and Mathematics

Language

English

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