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.009a" src="https://static.hindawi.com/articles/aaa/volume-2014/302982/figures/302982.fig.009a.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.009b" src="https://static.hindawi.com/articles/aaa/volume-2014/302982/figures/302982.fig.009b.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 angular velocity tracking error <svg height="13.1875" id="M275" style="vertical-align:-3.3907pt" version="1.1" viewbox="0 0 23.35 13.1875" width="23.35" xmlns="http://www.w3.org/2000/svg" xmlns:xlink="http://www.w3.org/1999/xlink">
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q-11 -37 -23.5 -100t-12.5 -92q0 -47 16.5 -71.5t44.5 -24.5q62 0 95.5 67t33.5 160q0 107 -63 152l1 9q14 14 45 14q29 0 57.5 -44t28.5 -114z" id="x1D714"></path></g>
<g transform="matrix(.012,-0,0,-.012,11.463,12.425)"><path d="M391 364q0 -28 -20.5 -53.5t-50 -43.5t-70 -34t-73.5 -25t-68 -17v-29q0 -48 20 -81t65 -33q73 0 157 76l16 -23q-107 -113 -221 -113q-21 0 -40.5 6.5t-39 22t-31.5 47t-12 75.5q0 69 33.5 139.5t95.5 114.5q77 55 143 55q42 0 69 -24.5t27 -59.5zM313 350
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</svg> with different disturbance and uncertain inertia.</table>

Abstract and Applied Analysis

fig9

Figure 9

Figure 9: Finite-Time Control for Attitude Tracking Maneuver of Rigid Satellite 