Итерационный метод оценивания угловых координат и угловых скоростей космическаого аппарата на основе интегральных уравнений движения

Abstract

Iteration method for spacecraft attitude parameters estimation was developed in the paper. Angular coordinates and angular velocities, which define the position of coordinate system related to the spacecraft with respect to the orbital coordinate system, are taken as state variables. New method, based on integral form of motion equations, is proposed.