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.002a" src="https://static.hindawi.com/articles/aaa/volume-2014/302982/figures/302982.fig.002a.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.002b" src="https://static.hindawi.com/articles/aaa/volume-2014/302982/figures/302982.fig.002b.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 sliding surface <svg height="12.9375" id="M267" style="vertical-align:-3.27605pt" version="1.1" viewbox="0 0 13.95 12.9375" width="13.95" xmlns="http://www.w3.org/2000/svg" xmlns:xlink="http://www.w3.org/1999/xlink">
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<g transform="matrix(.012,-0,0,-.012,7,12.312)"><path d="M384 0h-275v27q67 5 81.5 18.5t14.5 68.5v385q0 38 -7.5 47.5t-40.5 10.5l-48 2v24q85 15 178 52v-521q0 -55 14.5 -68.5t82.5 -18.5v-27z" id="x31"></path></g>
</svg> with different disturbance and uncertain inertia.</table>

Abstract and Applied Analysis

fig2

Figure 2

Figure 2: Finite-Time Control for Attitude Tracking Maneuver of Rigid Satellite 