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Created with Raphaël 2.2.03SepDelete de430.bspmainmainTotal Delta V calculations for the Earth to Mars transfer using a lunar gravity assist.Delete Total_Delta_V_Lunar_Assist.mPropagated orbit trajectory between Earth and Mars in heliocentric frame.Iterative solution to optimise lunar gravity assist and V-infinity globe calculations.Total Delta V calculations for the Earth to Mars transfer using no lunar gravity assist.Total Delta V calculations for the Earth to Mars transfer using no lunar gravity assist.Mars capture orbit.Optimal trajectory calculations between Earth parking orbit and leaving the SOI.Porkchop plots for the 2024-2028 launch window.MATLAB code for aerobraking calculations.Animation showing the changes in orbit for a spacecraft performing aerobraking manoeuvres.Function to calculate the true anomaly of a satellite around an orbit.Function to propagate the spacecraft orbit using 2 body problem theorem.Lambert solver using universal variables, to calculate orbits off all conic orbits. Kepler function.Geometry and orbital coefficient calculations for an orbit.Cursor function when studying .mat figures.Cursor function when studying .mat figures.Orbital coefficients to ECI frameCalculation of semi-major axis with different variables.Lambert Solver Final Position when leaving the SOI of a body.Delta V calculation for Pork Chop Plotsephemeris datamatlab toolkitGeneric Kernels Animation for the transfer trajectory between Earth and MarsAnimation of the orbits of Earth and MarsNASA Spice Toolkit used for ephemeris data of celestial bodies.The functions in this repository support iterative calculations.Trajectories of Earth and Mars around the Sun.Initial commit