In this video I go over what low thrust trajectories are, and how to implement them into OrbitPropagator. Low thrust can be used for orbit stationkeeping (orbit raising / adjusting due to orbital perturbations), as a main thrusting system (get to target orbit, reach escape velocity), and more. I go over how mass has to be added to the state variable, because the mass of the spacecraft changes over time due to expelling fuel from the spacecraft, and must be accounted for. I also go over useful plots when doing analysis of low thrust trajectories.
Pre-req videos:
1. Introduction / Overview - [ Ссылка ]
2. Two Body Problem / ODE Solvers - [ Ссылка ]
3. Developing the 3D Plotting Function - [ Ссылка ]
4. Developing the OrbitPropagator Class and the Planetary Data File - [ Ссылка ]
5. tools.py and the plot_n_orbits() function - [ Ссылка ]
8. J2 Perturbation - [ Ссылка ]
Optional videos:
6. Keplerian Orbital Elements - [ Ссылка ]
9. rv2coes() Function - [ Ссылка ]
10. Plotting the Keplerian / Classical Orbital Elements - [ Ссылка ]
Low Thrust Trajectories | Orbital Mechanics with Python 13
Теги
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