Modeling the shape correction of a thin-walled composite reflector of a spacecraft

This paper examines an adjustable thin-wall composite reflector for a small satellite. The reflector consisted of 6 identical sectors which had 4 adjusting units in the form of linear actuators. The purpose of this work was to explore the capabilities of numerical modeling to ensure the shape correction of the reflector using adjusting units. For this purpose, two sketch models were presented corresponding to the stages of the design life cycle. The mold model was used to calculate the residual deformations after manufacturing of the reflector in an autoclave. The orbital model was used to calculate temperature deformations of the reflector over time under a variable solar flux. For each of these models a series of optimizations were performed by the Nelder-Mead method. As a result, the positions of the adjustment units were determined, which provide the minimal standard deviation of the reflector shape from paraboloid. The calculations showed that the optimal adjustments can significantly compensate for the deformations of the reflector and increase its shape stability both after molding and during orbital flight. Thus, the presented method of multifactor numerical analysis can be promising for creating a shape correction system of the reflector at its main life stages.