Aerospace Trajectory Optimization - OTB
Updated 30 Dec 2019
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.
David Eagle (2022). Aerospace Trajectory Optimization - OTB (https://www.mathworks.com/matlabcentral/fileexchange/73805-aerospace-trajectory-optimization-otb), MATLAB Central File Exchange. Retrieved .
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