Thermal deformation suppression method based on active heat flow

The invention relates to a thermal deformation suppression method based on active heat flow. The method comprises the following steps: establishing a finite element model of a spacecraft structure; n mounting points loaded on the spacecraft structure are selected, and three-dimensional displacement vectors u (t) of the n mounting points are established; applying a temperature load to the finite element model to obtain unit strain and temperature information under different temperature load conditions, and further obtaining three-dimensional displacement of n mounting points and outputting the three-dimensional displacement to u (t); according to the control heat flow and the difference between the displacement of the n mounting points under the control heat flow and the displacement target value, an optimal control discrete equation is established and iteratively solved, and the optimal control heat flow is obtained; the optimal control heat flow is loaded to the m selected positions, and thermal deformation