Conceptual design of the spacecraft attitude control based on the plane displacement of the propulsion system

One of the important factors in the design of spacecraft is the efficient selection of spacecraft attitude control system. In some cases, due to the mission of spacecraft, several status control systems are used in combination. The achievement of practical and efficient methods as well as new methods in subsystem of state control is of particular importance. Therefore, studies and researches carried out in this field are often applied to improve the efficiency of state control and optimization methods from parameters such as fuel consumption, time, and cost. In this research, possibility of realizing the design of the spacecraft control system through the displacement of main engine will be examined. It is necessary to reduce equipment and systems of the state control subsystem, including: (thrusters, fuel transfer pipes, automatic valves, nozzles, power transmission cables, control signals, and structural complexities). Realizing the above-mentioned requirement in spacecraft will reduce the weight, cost, and complexity of the instruments.