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N-body Gravity Assist Trajectory Analysis

version 1.0.0 (51.2 KB) by David Eagle
Divide-and-conquer approach to solving a single gravity assist interplanetary trajectory subject to n-body perturbations

25 Downloads

Updated 22 Mar 2021

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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.

Cite As

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 .

MATLAB Release Compatibility
Created with R2019b
Compatible with any release
Platform Compatibility
Windows macOS Linux

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