This paper designs a control law for thrust vector aircraft using Incremental Dynamic Inversion (IDI), addressing traditional flight control challenges due to aircraft's complex structures and nonlinear dynamics, especially in stall maneuvers. The research innovatively applies dynamic inversion for adaptability. By analyzing pitch, roll, and yaw motions, the study establishes a control law design achieving full axis decoupling and efficient control in high dynamic conditions. The aircraft's dynamic model, characterized by time-variable, nonlinear state variables and control inputs, is effectively managed using IDI, significantly improving robustness and control precision. Simulation results demonstrate the system's performance in maintaining stability and control under complex dynamic conditions. This research offers a robust, adaptable methodology for aircraft control law design, significantly improving over traditional PID controllers in tracking efficiency and effectiveness in nonlinear regimes.