Simultaneous control of centre of mass and around centre of mass motion during sc maneuvers performance on geosynchronous and high elliptic orbits using electric rocket engines

Developed are spacecraft (SC) inertial actuator angular momentum control algorithms in performance of in-orbit maneuvers using electric rocket engines arranged according to configuration which enables to simultaneously develop forces and control moments relative to SC centre of mass. Presented are the results of geosynchronous SC Yamal-202 flight-design tests, as well as mathematical modeling of high-elliptic orbit-based advanced SC maneuvers.