| 摘要 |
<p>This system provides a fuel efficient way to change the inclination of an orbiting satellite. This is done by an indirect route by first doing a maneuver to bring the satellite to the moon on a BCT (Ballistic Capture Transfer). At the moon, the satellite is in the fuzzy boundary or weak stability boundary. A negligibly small maneuver can then bring it back to the Earth on a reverse BCT to the desired Earth inclination. Another maneuver puts it into the new ellipse at the Earth. Satellites that are launched into a LEO in a circular orbit of an altitude of 700 km with an inclination of 34°, approximately 6 km/s is required to change the inclination to 90°. This method achieves a significant savings and unexpected benefits in energy as measured by Delta-V. Flight time is substantially reduced from the previous method of 170 days to 88 or even 6 days.</p> |
