| Citation: | YU H F，GUO Y Q，WANG J M. Mode transition control of over-under TBCC under variable Mach number[J]. Journal of Beijing University of Aeronautics and Astronautics，2024，50（11）：3456-3462 （in Chinese） doi: 10.13700/j.bh.1001-5965.2022.0827
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With the development of hypersonic technology, turbine-based combined cycle (TBCC) engines have received much attention. Mode transition is one of the obstacles that restrict the application of TBCC engines. Therefore, it is necessary to study the control methods in this process. First, a model synthesis method was proposed, which realized the comprehensive iteration of a one-dimensional inlet, ramjet, and turbine engine. A TBCC model suitable for control system design was constructed based on the MATLAB/Simulink environment. Then, the single mode control system was analyzed, and a mode transition controller structure was proposed following the principle of minimal modification. The controller design method was developed by linear matrix inequality (LMI) tool. Finally, the significance of variable Mach number simulation was illustrated. The control system was verified by mode transition simulation at Mach number of 2.5–3. The simulation result shows that the control system can ensure the safety of TBCC engines, and the thrust fluctuation is less than 4.2% in the variable Mach number mode transition stage.
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