Use of jet engines for orbiral movement control of a spacecraft, simultaneously with dumping the momentum of electromechanical actuators

We consider a system of eight jet engines that is meant to control a spacecraft motion. Tractive forces of the engines have a central symmetry with respect to the spacecraft mass center and have bilateral symmetries with respect to coordinate planes of some frame whose origin is in this center. We investigate the feasibility of such a system to form a prescribed force impulse simultaneously with dumping the angular momentum of spacecraft electromechanical actuators. We derive the formulas that enable optimizing the system parameters and modes of its operations.