Mathematical Models of a Solar Sail Spacecraft Controlled Motion

Abstract

The features of a solar sail Spacecraft control and the possibilities to take into account the translational and rotational motion are considered. Based on the approximation of the motion equations for various orbits and body parameters, control possibilities and conditions for the stability of motion in given orbits as well as in the vicinity of libration points are discussed.To control the Spacecraft motion you can change the size, shape, surface properties or orientation of the sail elements relative to the flow of sunlight. The equations of motion can be presented based on a model of the problem of two bodies moving in a Central gravitational field, taking into account perturbations. When creating geosynchronous orbits in the vicinity of the Earth or for placing the Sun-Earth-Spacecraft system at libration points, a more general model of the photogravitational restricted three-body problem should be used.To obtain control capabilities and stability conditions for the motion in the specified orbits, as well as in the vicinity of collinear or triangular libration points, we do approximation of the perturbed motion equations system for different orbits and parameters of the main bodies. The stability of the Spacecraft sails system orientation is provided by the forces moments relative to the center of mass.