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.
Repository Citation
Srinivasan, L.,
Singh, S. N.
(2014).
Robust Output Feedback Attitude Control of Spacecraft Using Solar Radiation Pressure.
23rd International Conference on Systems Engineering
Springer-Verlag.
