This project was to determine the six Keplerian orbital elements of a satellite's from 3 initial angle-only observations. We also propagate the satelite's orbit forward in time using ODE45, but we included the Keplerian method of propogation since it is discussed in the report.
For an example of how to run this program run main.m
This determins orbits of 2 different sattelites from the same observation point in Tucson, AZ.
- Tristan Schuler - University of Arizona
- Jakob Hammes - University of Arizona
- Steven Anderson - University of Arizona