Optimal Finite-burn Interplanetary Injection from Earth Orbi

A MATLAB script for optimizing finite-burn interplanetary injection trajectories (SNOPT version).
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Updated 1 May 2021

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PDF document and MATLAB script named escape.m that can be used to analyze a finite-burn maneuver that achieves interplanetary injection from an initial Earth park orbit. The simulation assumes the propulsive maneuver is continuous, coplanar and modeled as a series of optimal discretized steering angles. This script attempts to minimize the scalar magnitude of the finite-burn while solving for user-defined “boundary conditions” or hyperbolic targets.
The orbital motion is modeled using modified equinoctial orbital elements and the script assumes that the thrust magnitude is constant during the entire orbit transfer. Initial guesses for the escape.m script can be determined using the hyper1.m script, “Impulsive Hyperbolic Injection from a Circular Park Orbit”. This MATLAB script provides the park orbit right ascension of the ascending node (RAAN) and the true anomaly of the impulsive injection maneuver on the initial circular park orbit.

Cite As

David Eagle (2024). Optimal Finite-burn Interplanetary Injection from Earth Orbi (https://www.mathworks.com/matlabcentral/fileexchange/42215-optimal-finite-burn-interplanetary-injection-from-earth-orbi), MATLAB Central File Exchange. Retrieved .

MATLAB Release Compatibility
Created with R2019b
Compatible with any release
Platform Compatibility
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Version Published Release Notes
1.6.0.0

Added fixed thrust duration example.

1.5.0.0

Update of source code and PDF documentation

1.4.0.0

General software updates

1.3.0.0

General update of main script software and support functions.

1.2.0.0

Changed objective function to thrust duration. Updated PDF. Added main script (escape_64bit.m) that uses the March 17, 2014 version of SNOPT.

1.1.0.0

Option added to read and use a csv data file for the initial guess. Also writes a data file of the current simulation.

1.0.0.0