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N-body Gravity Assist Trajectory Analysis - OTB version

version 1.0.0 (13.2 MB) by David Eagle
Divide-and-conquer approach to solving a single gravity assist interplanetary trajectory subject to n-body perturbations

9 Downloads

Updated 19 May 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. Examples are included for a Earth departure, Venus flyby and Mars arrival trajectory. Each n-body trajectory "leg" is optimized using the Optimization Toolbox. 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 - OTB version (https://www.mathworks.com/matlabcentral/fileexchange/92523-n-body-gravity-assist-trajectory-analysis-otb-version), MATLAB Central File Exchange. Retrieved .

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

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