Analysis and simulation of orbits in the circular-restricted three-body problem (CRTBP), where primary and secondary bodies move in circular orbits about the common center of mass, and effect of gravitational attraction of the smallest body are ignored. The applications described here are for orbital problems in the Sun-Earth-Moon system, whose
trajectory was simulated in MATLAB.
The symbolic Toolbox was used to solve non linear second order differential equations.
hello man great work!can you please answer some questions?
firstly,where did you find the equations of motion for this system.
secondly,are these equations general?i mean can they be used to describe another system like sun-jupiter-satellite or sun-earth-asteroid just by changing the mass and orbit constants?or i have to change the whole dynamical system?
thanx a lot,
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