Aerospace Trajectory Optimization - OTB

Demonstrates the solution of an aerospace trajectory optimization problem.
Updated 30 Dec 2019

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Optimization Toolbox version of the MATLAB script that demonstrates aerospace trajectory optimization using direct transcription and collocation. In the language of optimal control theory, this problem is a “continuous system with functions of the state variables prescribed at a fixed terminal time”. The numerical example given in the text is a continuous, low-thrust coplanar orbit transfer from Earth to Mars. The orbits of the planets are assumed to be circular and coplanar, and the total transfer time is about 193 days.

Cite As

David Eagle (2024). Aerospace Trajectory Optimization - OTB (, MATLAB Central File Exchange. Retrieved .

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

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