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.006a" src="https://static.hindawi.com/articles/aaa/volume-2014/302982/figures/302982.fig.006a.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.006b" src="https://static.hindawi.com/articles/aaa/volume-2014/302982/figures/302982.fig.006b.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="M272" 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">
<g transform="matrix(.017,-0,0,-.017,.625,8.6)"><path d="M548 455q-32 -77 -74 -77q-37 0 -103 10l-3 -2q36 -30 48.5 -62t12.5 -80q0 -103 -75 -179.5t-175 -76.5q-70 0 -113 45t-43 128q0 115 83.5 200.5t209.5 85.5q31 0 77.5 -4t67.5 -4q36 0 62 30zM350 274q0 54 -17 86q-19 35 -57 35q-50 0 -90 -37.5t-59 -91.5t-19 -109
q0 -61 24.5 -96.5t65.5 -35.5q51 0 87.5 46.5t50.5 100.5t14 102z" id="x1D70E"></path></g>
<g transform="matrix(.012,-0,0,-.012,10.225,12.675)"><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
q0 26 -14.5 40.5t-37.5 14.5q-32 0 -44 -7q-82 -46 -104 -175q200 49 200 127z" id="x1D452"></path></g><g transform="matrix(.012,-0,0,-.012,15.151,12.675)"><path d="M412 140l28 -9q0 -2 -35 -131h-373v23q112 112 161 170q59 70 92 127t33 115q0 63 -31 98t-86 35q-75 0 -137 -93l-22 20l57 81q55 59 135 59q69 0 118.5 -46.5t49.5 -122.5q0 -62 -29.5 -114t-102.5 -130l-141 -149h186q42 0 58.5 10.5t38.5 56.5z" id="x32"></path></g>
</svg> with different disturbance and uncertain inertia.</table>

Abstract and Applied Analysis

fig6

Figure 6

Figure 6: Finite-Time Control for Attitude Tracking Maneuver of Rigid Satellite 