In this video I go over stop conditions to orbit propagation, and how to implement them into OrbitPropagator.
Stop conditions can be used in many applications, such as: checking if spacecraft deorbited (at Earth, a spacecraft is considered deorbited at 100km altitude, but on bodies without atmospheres that would be the surface), check if you need an orbit boost because of orbit degradation due to aerodynamic drag, to know how long to thrust for when orbit raising, to check if you have reached escape velocity, and more.
I go over an old method that I used to use for implementing stop conditions, and why I feel like the new method that I have is better.

Pre-req videos:
1. Introduction / Overview - [ Ссылка ]
4. Developing the OrbitPropagator Class and the Planetary Data File - [ Ссылка ]

Optional videos:
2. Two Body Problem / ODE Solvers - [ Ссылка ]
3. Developing the 3D Plotting Function - [ Ссылка ]
5. tools.py and the plot_n_orbits() function - [ Ссылка ]
6. Keplerian Orbital Elements - [ Ссылка ]
8. J2 Perturbation - [ Ссылка ]
9. rv2coes() Function - [ Ссылка ]
10. Plotting the Keplerian / Classical Orbital Elements - [ Ссылка ]
13. Low Thrust - [ Ссылка ]

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