Solar sail spatial position control
Dynamics, ballistics, movement control of flying vehicles
The solar sail, represented in the form of a thin rotating mirror film attached to a cylindrical rigid insertion, is considered. The flywheel is introduced to compensate the kinetic moment of the “rigid insertion—film” system. The author suggests to use albedo’s changes for creating the control moment. It will result in the structure elements’ kinetic moments vectors non-collinearity. As a result, the spacecraft will start rotating around the axis coinciding with the sum of these vectors. To study the advantages of the described control method, an assessment of the time and energy required for the solar sail reorientation in the case of a structure without compensating flywheel and with its presence is made. It is established, that the change in the angular velocity of the “rigid insert—film” system due to the tangential component of the light pressure force is 0.01% of the initial value. In view of this value’s smallness, a decision was taken to neglect it in the further investigation.
The shape of the film surface under the effect of the gyroscopic moment occurring while the sail surface albedo changing was established. The dependence of the film deviation from the plane of the rigid inserting from the angular velocity of the sail turn was obtained. The results of the conducted studies reveal that for a solar sail with a flywheel the turn time decreased by more than two times, and energy consumption decreased almost by factor of seven, compared to the solar sail structure without a flywheel.
Keywords:solar sail, the control of a spacecraft, change of the reflectivity
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