Cruise missile , comprising: a fuselage which defines a longitudinal missile axis (L1) and forms an interior ; a fuel tank , arranged in the interior , for receiving liquid fuel (P); an engine arranged at a rear end of the fuselage ; a fuel pump for conveying liquid fuel (P) from the fuel tank into the engine ; at least two control fins , arranged in the region of the rear end of the fuselage and radially spaced apart therefrom; at least two aerofoils , radially spaced apart from the fuselage and arranged between the control fins and a front end of the fuselage in terms of the longitudinal projectile axis (L1); an actuator system , kinematically coupled to the aerofoils , for moving the aerofoils relative to the fuselage in such a way that a sweep angle (α) of the aerofoils relative to the longitudinal projectile axis (L1) is variable; and a control device which is set up: - to provide pump control signals (S5) for controlling a fuel conveyance rate of the fuel pump , - to determine a current fuel mass present in the fuel tank from the pump control signals (S5), - to determine a current position of a centre of mass (GC) of the cruise missile in terms of the longitudinal projectile axis (L1) from the determined current fuel mass; and - to generate actuator control signals (S8) for actuating the actuator system , so as to set a current position of an aerodynamic pressure point (CP) of the cruise missile in terms of the longitudinal missile axis (L1) as a function of the current position of the centre of mass (GC). a fuselage which defines a longitudinal missile axis (L1) and forms an interior ; a fuel tank , arranged in the interior , for receiving liquid fuel (P); an engine arranged at a rear end of the fuselage ; a fuel pump for conveying liquid fuel (P) from the fuel tank into the engine ; at least two control fins , arranged in the region of the rear end of the fuselage and radially spaced apart therefrom; at least two aerofoils , radially spaced apart from the fuselage and arranged between the control fins and a front end of the fuselage in terms of the longitudinal projectile axis (L1); an actuator system , kinematically coupled to the aerofoils , for moving the aerofoils relative to the fuselage in such a way that a sweep angle (α) of the aerofoils relative to the longitudinal projectile axis (L1) is variable; and a control device which is set up: - to provide pump control signals (S5) for controlling a fuel conveyance rate of the fuel pump , - to determine a current fuel mass present in the fuel tank from the pump control signals (S5), - to determine a current position of a centre of mass (GC) of the cruise missile in terms of the longitudinal projectile axis (L1) from the determined current fuel mass; and - to generate actuator control signals (S8) for actuating the actuator system , so as to set a current position of an aerodynamic pressure point (CP) of the cruise missile in terms of the longitudinal missile axis (L1) as a function of the current position of the centre of mass (GC). - to provide pump control signals (S5) for controlling a fuel conveyance rate of the fuel pump , - to determine a current fuel mass present in the fuel tank from the pump control signals (S5), - to determine a current position of a centre of mass (GC) of the cruise missile in terms of the longitudinal projectile axis (L1) from the determined current fuel mass; and - to generate actuator control signals (S8) for actuating the actuator system , so as to set a current position of an aerodynamic pressure point (CP) of the cruise missile in terms of the longitudinal missile axis (L1) as a function of the current position of the centre of mass (GC). <EOS>