Broad Flight Envelope Acceleration Control Method of Aero-Engine Based on Multiperiod Optimization Strategy

Abstract A new method based on a multiperiod optimization strategy is proposed to address the limited aero-engine acceleration performance across a broad flight envelope due to the traditional point-by-point optimization strategy for acceleration control law. First, the acceleration control law optimization method based on a multiperiod optimization strategy is introduced. This method takes multiperiod control variables as decision variables, aiming to solve the acceleration control law from a global optimization perspective and directly target the objective. Additionally, the mathematical model of the acceleration control law optimization problem is derived, demonstrating that this optimization problem can be transformed into a quadratic programing (QP) problem. Second, the design method for the engine broad flight envelope acceleration control plan is studied by isotherm correction to apply the acceleration control law to the broad flight envelope. Finally, simulation analysis indicates that under the ground standard condition (H = 0 km, Ma = 0, Tt2 = 288.15 K), the multiperiod optimization strategy reduces the acceleration adjustment time by 9.431% compared to the traditional acceleration control law optimization method. The multiperiod optimization strategy significantly improves the engine acceleration performance and the compressor stability margin. The study also validates the applicability and feasibility of the broad flight envelope acceleration control method based on isotherm correction.