Parameter optimal control has the advantage of often being easier and faster to
solve than general optimal control methods, and may be better suited to the task of
spacecraft re-entry trajectory optimization. In this thesis, a parameter optimal control
algorithm is implemented in MATLAB® to optimize a 2-D re-entry trajectory simulated
via Simulink®. Simulation results are validated by comparison with data from the flight
of Apollo 4. Behavior of the algorithm is observed as it optimizes the control input under
different conditions without constraints applied. The performance of the optimization
program is observed as the complexity of the control input is increased up to the point
where constraints are required to continue the optimization process. Finally, a guide is
laid out for further development of the algorithm towards both pre-flight trajectory
planning and real-time control applications for re-entry.
University of Minnesota M.S. thesis. May 2010. Major: Aerospace Engineering and Mechanics. Advisors:Dr. William Garrard, Dr. Yiyuan Zhao. 1 computer file (PDF); x, 113 pages, appendices A-F. Ill. (some col.)
Tetzman, Derrick G..
Simulation and optimization of spacecraft re-entry Trajectories.
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