Program control of a spacecraft with electric propulsion engines in the vicinity of an asteroid

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Resumo

The article considers the control of the center of mass motion of a spacecraft with a low-thrust propulsion system in the vicinity of an irregularly shaped asteroid. Formation of the motion control program during mission planning is complicated by incomplete knowledge of the asteroid’s gravity. A superposition of N attractive points rotating with the asteroid’s own angular velocity at a constant distance can be used as a mathematical model of the asteroid’s gravitational potential. A preliminary study of the research object allows calculating the characteristics of such a model with two attractive centers. Software control in the vicinity of the asteroid for target maneuvers is formed on the basis of a combination of locally optimal control laws and the developed algorithm of relay switching between them with a dead zone. The developed algorithms and methods are illustrated by the results of modeling the spacecraft motion in the vicinity of the asteroid 433 Eros.

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Sobre autores

O. Starinova

Samara National Research University

Autor responsável pela correspondência
Email: Starinova.OL@ssau.ru
Rússia, Samara

D. Chen

Nanjing University

Email: Starinova.OL@ssau.ru
República Popular da China, Nanjing

P. Fadeenkov

Samara National Research University

Email: Starinova.OL@ssau.ru
Rússia, Samara

Bibliografia

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2. Fig. 1. Rectangular and combined barycentric coordinate systems used to describe object-centric motion.

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3. Fig. 2. Algorithm and calculation results: a – algorithm for calculating the parameters of the gravitational field model, b – obtained isolines of the gravitational potential of the asteroid Eros.

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4. Fig. 3. Components of the dimensionless gravitational acceleration for the asteroid Eros: a – radial, b – transverse and normal.

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5. Fig. 4. Algorithm for selecting the values of the control functions.

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6. Fig. 5. Maneuver for forming a working object-centric orbit: a – control program, b – motion trajectory.

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7. Fig. 6. Orbit maintenance (first method): a – orbit-stabilizing control, b – change in orbit radius.

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8. Fig. 7. Orbit maintenance (second method): a – program of switching on and off the propulsion system, b – change of the orbit’s semi-major axis.

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