<p>To fully harness the performance potential of the engine within the broad flight envelope and achieve integrated control of the flight/propulsion system, a study on performance seeking control of the aeroengine based on an improved parameter correction model is conducted. To address the challenge of balancing real-time performance and convergence in the traditional performance seeking control method, an optimization model based on improved parameter correction methods is proposed. Furthermore, this study further addresses the issue of suboptimal convergence in the traditional linear programming algorithm caused by the fixed linearization intervals. An adaptive adjustment mechanism for linearization intervals is proposed, and the convergence and real-time performance of the method are systematically analyzed and validated. Simulation results demonstrate that, under the typical operating points, the three performance seeking control modes can increase the engine thrust by 7.368%, reduce the specific fuel consumption by 1.805%, and decrease the turbine inlet temperature by 3.098&#xa0;K, respectively. Across the broad flight envelope, the three modes can improve thrust by up to 7%, reduce the specific fuel consumption by up to 7%, and reduce the turbine inlet temperature by up to 47.34&#xa0;K, demonstrating excellent robustness. The proposed performance seeking control method achieves steady-state optimal control of the thrust, the specific fuel consumption, and the turbine inlet temperature across the broad flight envelope, offering significant potential for engineering application in the field of integrated flight/propulsion control.</p>