Aerospace Trajectory Optimization - OTB

バージョン 1.0.0 (628 KB) 作成者: David Eagle
Demonstrates the solution of an aerospace trajectory optimization problem.
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更新 2019/12/30

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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.

引用

David Eagle (2024). Aerospace Trajectory Optimization - OTB (https://www.mathworks.com/matlabcentral/fileexchange/73805-aerospace-trajectory-optimization-otb), MATLAB Central File Exchange. 取得済み .

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