Optimal control of spacecraft motion in the vicinity of Eros 433 asteroid

Abstract


The article describes an algorithm for optimizing controlled motion of a spacecraft equipped with low-thrust electric propulsion engines maneuvering in the vicinity of an object with an irregular gravitational field (asteroid Eros 433). A mathematical model of the object’s gravitational potential and a model of spacecraft motion are presented. The Pontryagin maximum principle is used to get the time-optimal control program. The formulated boundary value problem is solved numerically by the modified Newton method. The described algorithm can be used to solve similar problems of low-thrust flight dynamics in the vicinity of objects with irregular gravitational fields.


About the authors

A. Yu. Shornikov

Samara National Research University

Author for correspondence.
Email: andreishornikov@gmail.com

Russian Federation

Postgraduate Student, Department of Space Engineering

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