Finite-Time Control for Attitude Tracking Maneuver of Rigid Satellite

<table class="table-group" width="800px"><tr class="fig-image" id="a"><td><img alt="302982.fig.005a" src="https://static.hindawi.com/articles/aaa/volume-2014/302982/figures/302982.fig.005a.jpg"/></td></tr><tr class="fig-caption"><td align="center"><table><tr><td><b>(a) </b>The whole response</td></tr></table></td></tr><tr class="fig-image" id="b"><td><img alt="302982.fig.005b" src="https://static.hindawi.com/articles/aaa/volume-2014/302982/figures/302982.fig.005b.jpg"/></td></tr><tr class="fig-caption"><td align="center"><table><tr><td><b>(b) </b>The steady-state behavior</td></tr></table></td></tr></table>

<table>The attitude tracking error <svg height="13.4375" id="M271" style="vertical-align:-3.3907pt" version="1.1" viewbox="0 0 22.112499 13.4375" width="22.112499" xmlns="http://www.w3.org/2000/svg" xmlns:xlink="http://www.w3.org/1999/xlink">
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</svg> with different disturbance and uncertain inertia.</table>

Abstract and Applied Analysis

fig5

Figure 5

Figure 5: Finite-Time Control for Attitude Tracking Maneuver of Rigid Satellite 