Efficiency of Hysteresis Rods in Small Spacecraft Attitude Stabilization

<table>Layouts studied: Cases A–C, calculated value of the effective magnetic fields, <svg height="18.112499" id="M119" style="vertical-align:-5.56921pt" version="1.1" viewbox="0 0 31.487499 18.112499" width="31.487499" 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,-.012,14.975,15.187)"><path d="M169 380l92 53q26 16 49 16q80 0 128.5 -56t48.5 -133q0 -108 -72.5 -180.5t-176.5 -91.5q-38 1 -69 18v-131q0 -57 13 -70t71 -18v-27h-236v27q49 5 61 17t12 61v452q0 48 -9.5 58.5t-56.5 16.5v24q66 11 145 43v-79zM169 346v-270q37 -39 94 -39q63 0 101.5 50
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</svg>, generated by the permanent magnet at both ends of the rods.</table>

The Scientific World Journal

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Figure 3

Figure 3: Efficiency of Hysteresis Rods in Small Spacecraft Attitude Stabilization 