The invention belongs to the technical field of aircraft residual control capability design, and particularly relates to an aircraft residual control capability evaluation method which comprises the following steps: an aerodynamic characteristic acquisition step: solving aerodynamic force, aerodynamic moment and aerodynamic derivative of an aircraft based on the relationship between aerodynamic force and aerodynamic moment and aircraft state and control surface deflection; a mathematical model establishing step: correcting the gravity center position of the aircraft based on an aircraft mass center motion equation and an aircraft mass center rotation equation, and introducing aerodynamic force and aerodynamic moment to establish an aircraft mathematical model; and a transverse course balancing step: carrying out transverse course balancing on the aircraft based on the aerodynamic derivative, thereby obtaining the remaining operation capability of the aircraft.