The present invention relates to a propulsion 
system of a vertical 
takeoff and landing aircraft or vehicle moving in any fluid or vacuum and more particularly to a 
vector control system of the vehicle propulsion thrust allowing an independent displacement with 
six degrees of freedom, three degrees of translation in relation to its centre of 
mass and three degrees of rotation in relation to its centre of 
mass. The aircraft displacement ability using the propulsion 
system of the present invention depends on two main thrusters or propellers and which can be tilted around 
pitch is (I) by means of tilting mechanisms and, used to perform a forward or backward movement, can be tilted around roll axis (X) by means of tilting mechanisms and, used to perform lateral movements to the right or to the left and to perform upward or downward movements (Z), the main thrusters being further used to perform rotations around the vehicle 
yaw axis (Z) and around the roll is (X). The locomotion function also uses one or two auxiliary thrusters or propellers and mainly used to control the rotation around the 
pitch axis, these thrusters or propellers and being fixed at or near the longitudinal is of the vehicle, with there thrust perpendicular or nearly perpendicular to the roll and 
pitch axis of the vehicle.