Abstract
An indirect optimization procedure is presented to minimize the propellant consumption for finite-burn transfers with two practical thrust control models, namely, inertially fixed thrust and fixed-plane linearly varying thrust direction. The optimality equations are derived with theory of optimal control and the consequent boundary value problem is solved with a procedure based on Newton's method. A homotopic approach is used to find suitable tentative solutions and assure convergence. The method is applied to the optimization of Moon escape trajectories with accurate dynamic models and proves to be fast and accurate.
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