The invention discloses an experiment module solar wing double-shaft
coupling sun-facing
fixed angle servo control method and
system, and aims to reduce
mechanical wear by reducing rotation of a solar wing, reduce
collision risk by reducing the projection area of the solar wing on an
orbital plane orthogonal plane, reduce physical damage on the basis of meeting the power requirement, and improve the reliability of the solar wing double-shaft
coupling sun-facing
fixed angle servo control system. The task requirement for long-life operation of the space
station is met, and the on-
orbit life of the solar wing of the space
station is prolonged. Namely, sun
orientation control is completed by adopting a fixed rotation angle value and an intermittent rotation mode for the
two degrees of freedom of the solar wing. The
design process comprises the steps that firstly, a beta axis is designed to be in a
fixed angle servo control mode, the rotation fixed angle of the beta axis is totally 2n + 1 gears, and the value range is {-n
delta,...,-3
delta,-2
delta,-delta, 0, delta, 2 delta, 3 delta,..., n delta}; when the beta axis does not
return to zero, setting the alpha axis to
return to zero horizontally; when the beta axis returns to zero, if the alpha axis returns to zero horizontally and cannot meet the power requirement, the alpha axis is designed to be in a fixed angle
servo control mode, the number of fixed rotation angles of the alpha axis is three, and the value range is {-
angle alpha0 ', 0 and
angle alpha0'}.