Abstract: The invention provides an aircraft attitude tracking control method, system and computer equipment, which belongs to the field of aircraft attitude control, comprising: obtaining aircraft operating parameters and establishing a kinematic model of the attitude tracking error of the aircraft. A specified time performance constraint function and attitude error boundary based on the hyperbolic cosecant composite function are then constructed. A constrained attitude error conversion function and its inverse function are utilized to obtain an unconstrained attitude tracking conversion error. Virtual control instructions are solved in kinematics using a sigmoid tracking differentiator to obtain a numerical derivative. The control moment in the dynamics is solved and the complete form of the attitude tracking algorithm is given for the aircraft attitude tracking system. This method provides a computationally efficient means of controlling aircraft to ensure that error convergence is achieved within a preset time.