Robust Output Feedback Attitude Control of Spacecraft Using Solar Radiation Pressure

Document Type

Conference Proceeding

Publication Date

8-21-2014

Publication Title

23rd International Conference on Systems Engineering

Publisher

Springer-Verlag

Abstract

The paper presents a robust nonlinear output feedback control system for the attitude control of satellites, with unstructured (unmodeled) dynamics in elliptic orbits, using solar radiation pressure. The nonaffine-in-control spacecraft model includes the gravity gradient torque, the control torque produced by two solar flaps, and external time-varying disturbance torque. The objective is to control the pitch angle of the spacecraft using the solar flaps. A robust feedback linearizing control law is derived for the trajectory control of the pitch angle. The controller includes a high-gain observer, which estimates the derivatives of the pitch angle as well as a lumped unstructured nonlinearity including the external disturbance moment in the pitch dynamics for synthesis. In the closed-loop system, the designed output feedback law accomplishes large angle rotational maneuvers. Simulation results are presented which show that in the closed-loop system, precise pitch angle control is accomplished, despite unmodeled nonlinearities and external disturbance torque in the model.

Disciplines

Electrical and Computer Engineering | Electrical and Electronics | Engineering

Language

English

Permissions

Use Find in Your Library, contact the author, or interlibrary loan to garner a copy of the item. Publisher policy does not allow archiving the final published version. If a post-print (author's peer-reviewed manuscript) is allowed and available, or publisher policy changes, the item will be deposited.


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