Circular Restricted Three Body Problem Orbit Propagator

Set of functions that plots the orbit of an object in a three body system. Libration points are calculated using Newton's Method and Jacobi's constant is calculated for the entire orbit. Utilizes non-dimensional constants. Generalizable for circular restricted three body problem. Functionality can be added to make it generalizable for elliptical restricted three body problems. Inputs are in dimensional unites while outputs are in non-dimensional and dimensional. All calculated variables are outputted for analysis and error checking.

These functions were made as a part of coursework for AE6614: Advanced Astrodynamics, Missouri University of Science and Technology, Spring 2021. Any errors made are that of myself and not the instruction of the course. This project was made to complete coursework requirements and does not constitute a verified professional orbit propagator.

Feedback and suggestions are welcome. Please report any errors or bugs found.