The attitude control of an Earth-pointing spacecraft in a circular orbit, subject to the gravity-gradient torque, is explored. The spacecraft attitude is described using the modified Rodrigues parameters. A series of controllers are designed using the nonlinear control methodology and are subsequently generated using a Taylor series expansion to approximate solutions of the Hamilton–Jacobi equations. These controllers are applied to the problem of Earth-pointing spacecraft in circular orbits. The controllers are compared using both input–output and initial condition simulations, in an effort to gauge the improvements made possible by nonlinear feedback.
Attitude control of Earth-pointing spacecraft using nonlinear control
01.10.2014
15 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Attitude control of Earth-pointing spacecraft using nonlinear [Formula] control
Online Contents | 2014
|Attitude control of Earth-pointing spacecraft using nonlinear H∞ control
Tema Archiv | 2014
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