Artificial Lagrange Points for Solar Sail with Electrochromic Material Panels

The aim of this Note is to explore the capabilities of the emerging EMP technology for the active stabilization of L1-type AEPs using a square solar sail with a fixed attitude. The problem is addressed within an elliptic restricted framework, which is a more realistic model with respect to the classical circular case [4]. The main spacecraft parameters, including the sail side and the total spacecraft mass, are defined, by means of a simplified mathematical model, as a function of the main mission requirements in terms of maximum allowed sail lightness number variation and AEP position.