Application of differential evolution algorithm in the problem of aeroassisted orbital plane change maneuver

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The paper deals with application of the differential evolution method in optimizing aeroassisted orbital plane change maneuver performed by an aerospace vehicle with a high lift-to-drag ratio. The vehicle’s motion relative to the Earth is described by a system of differential equations in the flight path axis system. The angle-of-attack and the air path bank angle control programs are presented in the form of Fourier series and thrust control has the form of flip-flop control. The results of solving problems without phase parameter constraints obtained by the differential evolution algorithm were compared with the results obtained using Pontryagin’s maximum principle. The solution of the optimization problem taking into account temperature limitations at the stagnation point was obtained on the basis of the differential evolution algorithm.

About the authors

N. A. Elisov

Samara National Research University

Author for correspondence.

Postgraduate Student of the Department of Space Engineering

Russian Federation

S. A. Ishkov

Samara National Research University


Doctor of Science (Engineering),
Professor of the Department of Space Engineering

Russian Federation

A. A. Khramov

Samara National Research University


Candidate of Science (Engineering),
Associate Professor of the Department of Space Engineering

Russian Federation


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