attitude control about at least one of the roll pitch and yaw axes is provided totally or partially by a system utilizing the variation of at least one of the components of the angular momentum onboard the satellite l attitude control during orbit control maneuvers is obtained by varying the three components of the onboard angular momentum and by minimizing disturbances by means of the invention m attitude control outside orbit control maneuvers is obtained using solar pressure in an embodiment that is not shown with the assistance of magnetic dipoles n in an embodiment that is not shown attitude control outside orbit control maneuvers is provided by magnetic dipoles possibly with the assistance of solar pressure o attitude control outside orbit control maneuvers is used to align the components of the onboard angular momentum with a set point value q all or some of the orbit control thrusters are of the low thrust type lt 1 newton r all or some of the orbit control thrusters are of the ionic type s all or some of the orbit control thrusters are of the electric arc ionization type and t all or some of the orbit control actuators are orientable surfaces exposed to the solar pressure the remainder of the description which refers to fig1 through 16 concerns an application wherein the orbit and attitude control propulsion system used in the operational phase does not use chemical propulsion it is therefore free of the drawbacks inherent to chemical propulsion such as risk of leaks sudden variations in attitude and or possible generation of.