Attitude guidance and control of the navigation satellites at a passage of the singular orbital sites

Abstract

The solar-terrestrial reference frame is applied during a navigation satellite flight using onboard measured units of  directions on the Sun and Earth, which are beginning in the satellite  (Object) mass center. The angle between these units traditionally is named as the angle SOE (Sun - Object - Earth). We consider problems of attitude guidance and control at  the spacecraft  operation on specific parts of the orbit (singular orbit sites)  at following values of the SOE angles --- close to 0 deg (small SOE angles) and  close to 180 deg  (large SOE angles) with a view to minimizing the impact of solar pressure forces on the SC mass center  motion.