Abstract
The paper considers a spatial controlled heliocentric Earth-Mars flight of the spacecraft with a non-perfectly reflecting solar sail. A new mathematical model of motion is described, taking into account the dynamics of motion relative to the center of mass under the action of forces and torques from light pressure. To implement the flight, a spacecraft control algorithm was formed based on local optimal control laws for the steepest change in osculating elements. The orientation of the solar sail is controlled by thin-film controls located around the perimeter of the solar sail surface. As a result of motion simulation, the duration and trajectory of the flight, the control program, and the necessary design parameters of the spacecraft with solar sail were determined.
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