Complex modeling behavior of the spacecraft's construction with a rotary solar sail

The article is devoted to the study of various aspects of the operation of the spacecraft's design for the solar sail of the rotor type in the near-earth orbit. The purpose of the operation is to deliver scientific equipment to a given point in space. The first stage of any research interplanetary mission is the exit from the action sphere of the Earth, which is a long and energy-intensive maneuver using multiple and fast enough software reversals of the sail's surface of the large area. This requires a joint analysis of the dynamics of spacecraft motion relative to the center of mass, strength and stability of the sail and other structural elements of the spacecraft. In this paper, such an analysis is carried out for a rotary solar sail spacecraft which is weighing 332 kg and has a total sail area of 184.2 m2. Design pattern under consideration coincides with the spacecraft IKAROS that Japan aerospace exploration Agency designed to study Venus. IKAROS was taken out of the action sphere of the Earth using the upper stage and avoided the motion in the gravitational field of the Earth with an open sail. Studies conducted in this work show that the height of the starting orbit significantly affects the parameters of the law of motion control. Higher geocentric orbits allow the use of software turns with lower angular velocities to perform the maneuver, which reduces the loads on the sail canvas from the forces of inertia. It was found that the CAS of this design can perform a target maneuver at a height of the starting orbit exceeding 20,000 km.