I shafieenejad - Department of Aerospace engineering, K. N. Toosi University of Technology
a.b novinzadeh - Department of Aerospace engineering, K. N. Toosi University of Technology
v.r molazadeh - Department of Aerospace engineering, K. N. Toosi University of Technology

The present research is intended to present an algorithm for solving the nonlinear closed-loop optimal control problem with regard to space trajectory design viewpoint. To do so, issues such as optimal control theory, three-dimensional Fourier series and evolutionary optimization as Imperialist competitive algorithm (ICA) are utilized. Attempts have been made to introduce a new and comprehensive algorithm to cover free-time problems in the optimal control theory for space manoeuvres. The algorithm presented was solved and validated for the Edelbaum orbital transfer problem as a case study in which nonlinear dynamic equations were included. Results regarding to the three-dimensional Fourier series and the optimization method as ICA are achieved. This novel method provides an accurate and precise solution for this particular closed-loop orbital optimal control problem, which satisfies the objective of this work. Finally, this novel and new method is introduced for space mission designers as efficient method to achieve closed-loop guidance.

Closed-loop; Optimal control; Space trajectory; ICA optimization; Three dimensional Fourier series