Boundary problem solution of an optimal control transfer between circular orbits for an electric propulsion spacecraft in an irregular gravitational field of an asteroid

• Main Authors: Shornikov, Andrey, Starinova, Olga
• Format: Conference Proceeding
• Language: English
• Subjects: Approximation; Circular orbits; Computer simulation; Electric propulsion; Gravitation; Gravitational fields; Mathematical models; Maximum principle; Object motion; Optimal control; Spacecraft motion; Spacecraft propulsion
• ISSN: 0094-243X; 1551-7616
• DOI: 10.1063/1.4972737

There is a problem to control spacecraft’s motion near objects with irregular gravitational fields as asteroids. In this paper we present a mathematical model of spacecraft motion with an electric propulsion engine in an irregular non-spherical gravitational field of the asteroid Eros 433. We propose to use the model of single gravity points for simulation of the motion of a spacecraft in the irregular gravitational field. The equations of spacecraft motion are corresponding equations of the n-body problem. A boundary task of the control spacecraft’s transfer between circular orbits from 200 km to 100 km is considered. Authors propose a combination of the Pontryagin’s maximum principle and the Newton’s step by step approximation as solutions methods for the boundary problem.