A method for stationing a satellite, comprising: - a first step of determining a predefined trajectory used for said stationing of said satellite based on a model of movement of said satellite; - a second step of determining parameters of the predefined control law of approximation of said predefined trajectory and minimizing an impact of said predefined control law on a deviation from a trajectory followed by said satellite using said parameters of the predefined control law, with respect to said predefined trajectory; characterized in that the method comprises the following iterative steps: a third step of determining a state vector of said satellite; a fourth step of determining a deviation between said state vector of said satellite and said predefined trajectory; a fifth step of determining Lagrange multipliers based on a current state vector of said satellite, on a deviation between said current state vector and the predefined trajectory and on said parameters of the predefined control law; a sixth step of determining the parameters of a current control law of engines based on said Lagrange multipliers and by derivation of a parameter representative of an effect of the engines on said real trajectory; a seventh step of controlling the engines based on said parameters of the current control law. - a first step of determining a predefined trajectory used for said stationing of said satellite based on a model of movement of said satellite; - a second step of determining parameters of the predefined control law of approximation of said predefined trajectory and minimizing an impact of said predefined control law on a deviation from a trajectory followed by said satellite using said parameters of the predefined control law, with respect to said predefined trajectory; characterized in that the method comprises the following iterative steps: a third step of determining a state vector of said satellite; a fourth step of determining a deviation between said state vector of said satellite and said predefined trajectory; a fifth step of determining Lagrange multipliers based on a current state vector of said satellite, on a deviation between said current state vector and the predefined trajectory and on said parameters of the predefined control law; a sixth step of determining the parameters of a current control law of engines based on said Lagrange multipliers and by derivation of a parameter representative of an effect of the engines on said real trajectory; a seventh step of controlling the engines based on said parameters of the current control law. a third step of determining a state vector of said satellite; a fourth step of determining a deviation between said state vector of said satellite and said predefined trajectory; a fifth step of determining Lagrange multipliers based on a current state vector of said satellite, on a deviation between said current state vector and the predefined trajectory and on said parameters of the predefined control law; a sixth step of determining the parameters of a current control law of engines based on said Lagrange multipliers and by derivation of a parameter representative of an effect of the engines on said real trajectory; a seventh step of controlling the engines based on said parameters of the current control law.