Aerospace Trajectory Optimization Using Direct Transcription and Collocation

Versión 1.3.0.0 (498 KB) por David Eagle
Demonstrates the solution of an aerospace trajectory optimization problem.
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Actualizado 7 jul 2014

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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.

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David Eagle (2024). Aerospace Trajectory Optimization Using Direct Transcription and Collocation (https://www.mathworks.com/matlabcentral/fileexchange/38936-aerospace-trajectory-optimization-using-direct-transcription-and-collocation), MATLAB Central File Exchange. Recuperado .

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Versión Publicado Notas de la versión
1.3.0.0

Added main script (dto_trap_64bit.m) that uses the March 17, 2014 version of SNOPT.
1.2.0.0

Spelling correction of the title
1.1.0.0

Updated PDF document and several m-files. Now includes graphic display of the heliocentric planet orbits and transfer trajectory. PDF document includes new dimensional analysis section, trajectory diagram, etc.
1.0.0.0