Kepler's laws applied to real orbits, the six classical orbital elements, why LEO, GEO, and sun-synchronous orbits each exist for a specific reason, and the delta-v cost of moving between orbits with a Hohmann transfer.
This module starts from Kepler's three laws and shows exactly how they explain a satellite's changing speed around an elliptical orbit and fix the altitude of a geostationary orbit at a single physics-determined number. From there it works through the classical orbital elements, the trade-offs behind LEO, GEO, and sun-synchronous orbit choices, and the delta-v budgeting and Hohmann-transfer logic behind moving a spacecraft from one orbit to another.
By the end of this module you should be able to explain why a sun-synchronous orbit's altitude and inclination are not free design choices, and why a plane-change burn is scheduled at apogee rather than perigee — reasoning this program's spacecraft-systems module later builds on directly.