A novel optimization acceleration control method for adaptive cycle engine during whole flight missions

Improving the flight performance of aircraft engines has long been a key focus in aviation technology research, particularly in terms of acceleration performance during high-maneuvering missions. As a primary candidate for future aero propulsion systems, the adaptive cycle engine (ACE) offers the potential to further enhance acceleration performance with its multiple variable geometry mechanisms. However, the current single variable (main fuel) acceleration control method used in turbofan engines limits the potential acceleration for ACE. To address this issue, the paper proposes a novel nested optimization acceleration control method for ACE, which accounts for the effects of specific variable geometric components, including the front variable area of bypass injector (FVABI), the rear variable area of bypass injector (RVABI) and low-pressure turbine (LPT) guide vanes. Compare with the traditional acceleration control method, the proposed acceleration control method effectively delays the onset of the compressor operating near the surge boundary during the acceleration process, which significantly improves engine acceleration response under different acceleration missions. Finally, the hardware in the loop (HIL) simulation verifies the feasibility of the above multivariable acceleration optimal method. From the simulation results, it could be seen that compared with the traditional control plan, the proposed acceleration optimization control has significantly reduced thrust response time by more than 30 %.