Spin-Stabilized Spacecrafts: Analytical Attitude Propagation Using Magnetic Torques

<table>Evolution of the declination (<svg height="10.7375" id="M163" style="vertical-align:-0.13794pt" version="1.1" viewbox="0 0 7.9875002 10.7375" width="7.9875002" xmlns="http://www.w3.org/2000/svg">
<g transform="matrix(1.25,0,0,-1.25,0,10.7375)">
<g transform="translate(72,-63.41)">
<text transform="matrix(1,0,0,-1,-71.95,63.6)">
<tspan style="font-size: 12.50px; " x="0" y="0">𝛿</tspan>
</text>
</g>
</g>
</svg>) and right ascension (<svg height="7.1750002" id="M164" style="vertical-align:-0.1254pt" version="1.1" viewbox="0 0 8.9375 7.1750002" width="8.9375" xmlns="http://www.w3.org/2000/svg">
<g transform="matrix(1.25,0,0,-1.25,0,7.175)">
<g transform="translate(72,-66.26)">
<text transform="matrix(1,0,0,-1,-71.95,66.44)">
<tspan style="font-size: 12.50px; " x="0" y="0">𝛼</tspan>
</text>
</g>
</g>
</svg>) of satellite spin axis for SCD2 and its mean deviation error.</table>

Mathematical Problems in Engineering

fig4

Figure 4

Figure 4: Spin-Stabilized Spacecrafts: Analytical Attitude Propagation Using Magnetic Torques 