Updated 22 Mar 2021
This MATLAB script implements a divide-and-conquer approach to solving a single gravity assist interplanetary trajectory subject to n-body perturbations. This example is for a Earth departure, Venus flyby and Mars arrival trajectory. Each optimization "leg" is optimized using the SNOPT nonlinear programming algorithm (http://scicomp.ucsd.edu/~peg/). The planetary ephemeris used in this script is based on JPL Development Ephemeris DE421. Documentation is forth coming.
David Eagle (2021). N-body Gravity Assist Trajectory Analysis (https://www.mathworks.com/matlabcentral/fileexchange/89137-n-body-gravity-assist-trajectory-analysis), MATLAB Central File Exchange. Retrieved .
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