@article{WANG2025, 
author = {Yifan WANG and Haoying CHEN and Xuankai LIU and Haibo ZHANG},
title = {Multi-mode acceleration optimization control for adaptive cycle engine based on variable geometry components},
year = {2025},
journal = {Chinese Journal of Aeronautics},
volume = {38},
number = {9},
keywords = {Adaptive cycle engine, Mode transition, Multivariate acceleration plan, Sequential quadratic planning, Variable geometry components},
url = {https://www.sciopen.com/article/10.1016/j.cja.2025.103460},
doi = {10.1016/j.cja.2025.103460},
abstract = {The acceleration and mode transition performance are two significant performances of Adaptive Cycle Engine (ACE). However, separating the processes of acceleration and mode transition will slow down the response speed of thrust. Therefore, this paper proposes a multi-mode acceleration optimization control method that simultaneously performs ACE acceleration and mode transition. Firstly, an ACE component model with inlet flow characteristics was established, and the performance before and after mode transition were analyzed. Secondly, the principle of ACE acceleration optimization was analyzed, and the Front Variable Area Bypass Injector (FVABI) and Mode Selection Valve (MSV) were adopted in the acceleration process. Finally, based on the Sequential Quadratic Programming (SQP) algorithm, considering the degradation effects of engine components, we optimize the acceleration control plan for fuel and variable geometry mechanisms. The simulation results show that at the subsonic cruise point, the ACE multi-mode acceleration optimization control method can shorten the acceleration time from idle to middle state by 30.33%, and accelerate the thrust response speed by 33.72%. When the compressor flow rate of ACE deteriorates by 2% and the high-pressure turbine efficiency deteriorates by 4%, the adaptive acceleration control plan increases the high-pressure speed by 2.13% and thrust by about 6.82%; within the flight envelope, the acceleration time is reduced by more than 25%, and the thrust response speed is increased by more than 20%.}
}