Effects of the Eccentricity of a Perturbing Third Body on the Orbital Correction Maneuvers of a Spacecraft

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</svg> (rad)</td><td align="center">Thrusting time (min)</td></tr><tr><td class="thead-hr" colspan="2"><hr/></td></tr><tr><td align="left">0.0001</td><td align="center">0.085</td></tr><tr><td align="left">0.0005</td><td align="center">0.426</td></tr><tr><td align="left">0.0010</td><td align="center">0.852</td></tr><tr><td align="left">0.0050</td><td align="center">4.270</td></tr><tr class="table-tr"><td colspan="2"><hr class="tbody-hr"/></td></tr></table></td></tr></table>

Time required by the low thrust maneuvers to correct the inclination.

Mathematical Problems in Engineering

tab4

Table 4

Table 4: Effects of the Eccentricity of a Perturbing Third Body on the Orbital Correction Maneuvers of a Spacecraft 